Reconfigurable unmanned aircraft system

ABSTRACT

A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission.

If an Application Data Sheet (ADS) has been filed on the filing date ofthis application, it is incorporated by reference herein. Anyapplications claimed on the ADS for priority under 35 U.S.C. § § 119,120, 121, or 365(c), and any and all parent, grandparent,great-grandparent, etc. applications of such applications, are alsoincorporated by reference, including any priority claims made in thoseapplications and any material incorporated by reference, to the extentsuch subject matter is not inconsistent herewith.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application claims the benefit of the earliest availableeffective filing date(s) from the following listed application(s) (the“Priority Applications”), if any, listed below (e.g., claims earliestavailable priority dates for other than provisional patent applicationsor claims benefits under 35 USC § 119(e) for provisional patentapplications, for any and all parent, grandparent, great-grandparent,etc. applications of the Priority Application(s)).

PRIORITY APPLICATIONS

[None]

The present application constitutes a continuation of U.S. patentapplication Ser. No. 14/560,606, entitled RECONFIGURABLE UNMANNEDAIRCRAFT SYSTEM, naming Alistair K. Chan, Jesse R. Cheatham III, Hon WahChin, William David Duncan, Roderick A. Hyde, Muriel Y. Ishikawa, JordinT. Kare, Tony S. Pan, Robert C. Petroski, Clarence T. Tegreene, David B.Tuckerman, Thomas Allan Weaver, Lowell L. Wood, Jr. As inventors, filed4 Dec. 2014, which is currently co-pending or is an application of whicha currently co-pending application is entitled to the benefit of thefiling date and is herein incorporated by reference in its entirety.

RELATED APPLICATIONS

(a) U.S. patent application Ser. No. 14/501,302, titled SYSTEM ANDMETHOD FOR ADMINISTRATION AND MANAGEMENT OF AN AIRSPACE FOR UNMANNEDAIRCRAFT, naming R. Hyde et al. as inventors, filed Sep. 30, 2014 isrelated to and incorporated by reference in the present application; (b)U.S. patent application Ser. No. 14/501,343, titled UNMANNED AIRCRAFTCONFIGURED FOR OPERATION IN A MANAGED AIRSPACE OF FLYWAY, naming R. Hydeet al. as inventors, filed Sep. 30, 2014 is related to and incorporatedby reference in the present application; (c) U.S. patent applicationSer. No. 14/501,365, titled SYSTEM AND METHOD FOR OPERATION OF UNMANNEDAIRCRAFT WITHIN A MANAGED AIRSPACE OR FLYWAY, naming R. Hyde et al. asinventors, filed Sep. 30, 2014 is related to and incorporated byreference in the present application; (d) U.S. patent application Ser.No. 14/546,487, titled SYSTEM AND METHOD FOR MANAGEMENT OF AIRSPACE FORUNMANNED AIRCRAFT, naming R. Hyde et al. as inventors, filed Nov. 18,2014 is related to and incorporated by reference in the presentapplication; (e) U.S. patent application Ser. No. TBD, titled SYSTEM ANDMETHOD FOR OPERATION AND MANAGEMENT OF RECONFIGURABLE UNMANNED AIRCRAFT,naming R. Hyde et al. as inventors, filed Dec. 4, 2014 is related to andincorporated by reference in the present application.

If the listings of applications provided above are inconsistent with thelistings provided via an ADS, it is the intent of the Applicant to claimpriority to each application that appears in the DomesticBenefit/National Stage Information section of the ADS and to eachapplication that appears in the Priority Applications section of thisapplication.

All subject matter of the Priority Applications and of any and allapplications related to the Priority Applications by priority claims(directly or indirectly), including any priority claims made and subjectmatter incorporated by reference therein as of the filing date of theinstant application, is incorporated herein by reference to the extentsuch subject matter is not inconsistent herewith.

BACKGROUND

The present invention relates to a reconfigurable unmanned aircraftsystem. The present invention also relates to a reconfigurable unmannedaircraft configured to operate in an airspace. The present inventionfurther relates to a system and method for configuring reconfigurableunmanned aircraft. The present invention further relates to a system andmethod for operation and management of reconfigurable unmanned aircraftin an airspace. The present inventions generally relate to improvementsto unmanned aircraft and for unmanned aircraft systems and methods.

It is known to use unmanned aircraft (e.g. referred to as unmannedair/aerial vehicle (UAV), unmanned aircraft system (UAS) to include anoperator/pilot at a remote location, drone, etc.). Such unmannedaircraft (UAV/craft or UAV/drone craft) at present exist in a widevariety of forms (shapes/sizes), types (e.g. winged craft, rotor-drivencraft, etc.), propulsion systems (e.g. engines, thrust-production,etc.), capacities, etc., with a wide variety of capabilities, carryingcapacities, control systems, telemetry systems, robustness, range, etc.,and as exist at present are able to perform a wide variety of functionsin military, commercial, and recreational applications. At present, thetypical UAV/drone craft is significantly smaller than a typical mannedaircraft and typically may lack the functionality of typical commercialaircraft; some UAV/drone craft have sophisticated on-board controlsystems; some UAV/drone craft are operated by pilots at remote stationswith data communications and instrumentation/feedback from the craft;other UAV/drone craft may have relatively simple control systems (e.g.basic remote control by line of sight by the operator). Differences inuse and operation of UAV/drone craft and typical manned aircraft allowfor differences in design and other design variations that facilitatefunctionality modifications and enhancements for UAV/drone craft.

The size and form and operation of UAV/drone craft are different fromtypical commercial aircraft and may vary significantly between types ofUAV/drone craft; UAV/drone craft may be provided in various forms,including in forms that range from relatively simple to relativelydifficult to control in flight conditions (and in comparison to atypical manned aircraft). Airworthiness/robustness,controllability/telemetry, data communications and failure modes forUAV/drone systems may vary widely between UAV/drone craft and incomparison to manned aircraft. Costs to build/purchase and operate aUAV/drone system may vary widely between UAV/drone craft and incomparison to manned aircraft. UAV/drone craft may be configured toperform functions for which a manned aircraft is generally not suitable(for various reasons) such as local/light parcel delivery,surveillance/monitoring, communications, military/government action,etc. UAV/drone craft may be designed and constructed to have widelyvaried capabilities for widely varied functions. Some UAV/drone craftmay be designed as “expendable” or for finite/one-time use; someUAV/drone craft may be designed for cost-efficiency and simplicity;other UAV/drone systems may be designed for lengthy useful lives inoperation.

It is known to provide a UAV/craft for use in any of a wide variety offunctions and operations including parcel/item delivery,monitoring/surveillance, data transmission/communications,hobby/entertainment, advertising/marketing, etc. Such known UAV craftare provided in a variety of types and forms of a basic type or sets oftypes. UAV/drone systems also have gained appeal in a segment of therecreation/hobby/toy industry.

One common form of UAV/craft is configured with a base and one or a setof rotors (e.g. to provide lift/thrust for propulsion) as in aconventional helicopter. It is known to design and construct such aUAV/craft in each of variety of designed arrangements given by apredetermined number of rotors, for example, with one rotor, two rotors,three rotors (tri-copter), four rotors (quad-copter), five rotors(penta-copter), six rotors (hexa-copter), eight rotors (octa-copter),etc.

Such known arrangements are by design and construction given apredetermined number of rotors in a predetermined position relative tothe base; such existing arrangements are not configured to be modifiedafter construction either in the number or placement of rotors; suchUAV/craft are constructed for stable operation as configured in terms ofrotor number/placement and do not comprise into use and operation asconstructed. Such UAV/craft are by design/construction generallyprovided with a design capability (within an operating range) forthrust/life, carrying payload, etc. and other flight characteristics.

It is known to provide an aircraft (such as UAV/drone craft) that can betransformed in form by reconstruction, see for example, U.S. PatentApplication Publication No. 20140263823 titled “Transformable AerialVehicle” and U.S. Pat. No. 7,922,115 titled “Modular UnmannedAir-Vehicle”. However, such known UAV/drone craft have limitations interms of transformability and/or functionality as implemented. Forexample, one method of transformation is to employ manual reconstructionof the arrangement of the UAV/craft, for example, rather than using acontrol/computing system. Such structures and systems for disassemblyand/or reassembly of a UAV/craft in implementation do not fully achieveavailable benefits of efficiency and performance if such structures andsystem for UAV/craft require manual intervention and/or substantial timeto implement a transformation.

One failure mode for UAV/craft is the failure of a rotor (e.g.malfunction of a rotor mechanism or motor/engine for a rotor/rotorsystem). If a UAV/craft suffers the malfunction/failure of a rotor andis not able to operate (e.g. to retain lift/thrust without the rotor),the likely result is that the UAV craft will be disabled or inoperable(and if failure occurs in flight the UAV/craft may crash land and/or belost). Such known UAV/craft may or may not be able to operatefunctionally without one or more rotors out of operation; any capabilityof transformation that such known UAV/craft may have is not ascompletely useful in a real-time situation of a rotor failure or rotormalfunction if the UAV/craft is unable to perform withoutservice/attention at a station (e.g. manual transformation/servicing ata station).

In use a UAV/craft may be called upon to carry payload/cargo that is ofa varied type or form; such payload may be widely varied in mass, size,form or shape, etc. Payload that is asymmetrical and/or that is notreadily able to be symmetrically located (in/on/under the base) relativeto the rotors may present mass balance difficulties for a UAV/craft; thepresence of an asymmetrical cargo may cause imbalances with respect tothe rotors and may affect stability, efficiency or possibly operabilityof the UAV/craft. Payload may be multi-component (e.g. multiple items)or have large mass; payload may be light-weight and flexible; payloadmay comprise fluid (e.g. subject to leaks, etc.) or solids (e.g. subjectto shifting in position). Depending upon how the payload is carried, apayload may provide inertia effects (e.g. lagging, swinging, sliding,etc.) in flight. Balancing the payload/cargo with respect to the rotorsof a multi-rotor UAV/craft may present difficulties in deployment of theUAV/craft (e.g. require surplus weight/mass and/or division/disassemblyof the items in the payload or other such action) before the UAV/craftmay begin the mission.

SUMMARY

Accordingly, it would be advantageous to provide a reconfigurableunmanned aircraft system. It would also be advantageous to provide areconfigurable unmanned aircraft configured to operate in an airspace.It would further be advantageous to provide a system and method forconfiguring a reconfigurable unmanned aircraft. It would further beadvantageous to provide a system and method for operation and managementof a reconfigurable unmanned aircraft in an airspace.

The present invention relates to an aircraft for unmanned flight that isselectively reconfigurable to modify flight characteristics. Theaircraft comprises a base, a first rotor on a first boom coupled to thebase, a second rotor on a second boom coupled to the base, and a thirdrotor on a third boom coupled to the base. Position of at least onerotor relative to the base can be modified by at least one oftranslation of the rotor relative to the boom; pivoting of the boomrelative to the base; translation of the boom relative to the base.Flight characteristics can be modified by configuration andreconfiguration of position of at least one rotor relative to the base.

The present invention relates to a selectively reconfigurable aircraftfor unmanned flight providing flight characteristics. The aircraftcomprises a base, a first rotor on a first boom coupled to the base, anda second rotor on a second boom coupled to the base. Position of thefirst rotor relative to the base can be modified by at least one oftranslation of the rotor relative to the boom; pivoting of the boomrelative to the base; translation of the boom relative to the base.Position of the second rotor relative to the base can be modified by atleast one of translation of the rotor relative to the boom; pivoting ofthe boom relative to the base; translation of the boom relative to thebase. Flight characteristics can be modified by reconfiguration of theposition of at least one rotor relative to the base.

The present invention relates to a method of reconfiguring selectivelyreconfigurable aircraft for unmanned flight. The method comprises thesteps of positioning a first rotor on a first boom coupled to the base,positioning a second rotor on a second boom coupled to the base, andmodifying the position of at least one rotor relative to the base.Position of the rotor relative to the base can be modified by at leastone of translation of the rotor relative to the boom; pivoting of theboom relative to the base; translation of the boom relative to the base.Flight characteristics can be modified by reconfiguration of theposition of at least one rotor relative to the base.

The present invention relates to a method of reconfiguring selectivelyreconfigurable aircraft for unmanned flight having a set of rotorsconfigured to provide lift for propulsion with at least one rotor thatis at least partially malfunctioning. The method comprises the steps ofidentifying the rotor that is malfunctioning, identifying at least onerotor that is able to function and is in an initial position, andrepositioning the at least one rotor that is able to function from theinitial position to a reconfigured position. The at least one functionalrotor when after reconfiguration in the reconfigured position is able tocompensate for the loss of function of the malfunctioning rotor.

The present invention relates to a method of operating a reconfigurablemulti-rotor unmanned aircraft with each rotor in a rotor position on amovable boom relative to a base of the aircraft for flight on a missionto provide intended flight characteristics in operating conditions. Themethod comprises the steps of configuring the aircraft in firstconfiguration with intended flight characteristics for ascent to start aflight and configuring the aircraft in a second configuration withintended flight characteristics for flight in operating conditions. Thefirst configuration comprises a first rotor position for at least onerotor. The second configuration comprises a second rotor position for atleast one rotor. Position of at least one rotor relative to the base canbe modified by at least one of translation of the rotor relative to theboom; pivoting of the boom relative to the base; translation of the boomrelative to the base.

The present invention relates to a method of configuring an aircrafthaving a set of repositionable rotors for unmanned flight on a missionto carry a payload from an initial configuration into a configurationfor the mission. The method comprises the steps of determiningproperties of the payload including at least mass properties,determining the manner in which the payload will be coupled to theaircraft, determining a configuration for the mission for each of therotors in the set of rotors at least partially in consideration of theproperties of the payload, and positioning the set of rotors into theconfiguration for the mission for the aircraft to perform the mission.

The present invention relates to a method of reconfiguring a selectivelyreconfigurable unmanned aircraft having a first rotor on a first boomcoupled to a base and a second rotor on a second boom coupled to thebase for a mission to carry a payload. The method comprises the steps ofdetermining the effect of the payload on flight characteristics andmodifying the position of at least one rotor relative to the base.Position of the rotor relative to the base can be modified by at leastone of translation of the rotor relative to the boom; pivoting of theboom relative to the base; translation of the boom relative to the base.Flight characteristics can be modified by reconfiguration of position ofat least one rotor relative to the base.

The present invention relates to a method of operating a reconfigurablemulti-rotor unmanned aircraft having flight characteristics for amission comprising flight with payload in operating conditions. Themethod comprises the steps of configuring the aircraft in an ascentconfiguration with flight characteristics for ascent to start a flightand configuring the aircraft in a first flight configuration with flightcharacteristics for flight in operating conditions. Configuring theaircraft comprises positioning of at least one rotor of the aircraftinto the configuration. Flight characteristics of the aircraft includeconsideration of properties of any payload carried by the aircraft.

The present invention relates to a selectively reconfigurable aircraftfor unmanned flight with payload providing flight characteristics. Theaircraft comprises a base, a first rotor on a first boom coupled to thebase, a second rotor on a second boom coupled to the base, and amonitoring system configured to monitor conditions of the aircraftincluding any payload. The payload comprises properties. Position of thefirst rotor relative to the base can be modified by at least one oftranslation of the rotor relative to the boom; pivoting of the boomrelative to the base; translation of the boom relative to the base.Position of the second rotor relative to the base can be modified by atleast one of translation of the rotor relative to the boom; pivoting ofthe boom relative to the base; translation of the boom relative to thebase. Flight characteristics can be modified by reconfiguration of theposition of at least one rotor relative to the base.

The present invention relates to a method of managing a fleet ofreconfigurable aircraft of a type having a set of rotors to providethrust for unmanned flight to perform a set of missions. The methodcomprises the steps of configuring a first aircraft in a firstconfiguration to perform a first mission and configuring a secondaircraft in a second configuration to perform a second mission. Thefirst aircraft is substantially the same as the second aircraft.Configuration of an aircraft comprises positioning at least one rotor ofthe set of rotors of the aircraft to provide for intended flightcharacteristics. Each of a plurality of aircraft in the fleet can beconfigured in a configuration to perform each of a plurality ofmissions.

The present invention relates to a selectively reconfigurable aircraftfor unmanned flight providing flight characteristics. The aircraftcomprises a base, a first rotor on a first boom coupled to the base, anda second rotor on a second boom coupled to the base. Position of thefirst rotor relative to the base can be modified by at least one oftranslation of the rotor relative to the boom; pivoting of the boomrelative to the base; translation of the boom relative to the base.Position of the second rotor relative to the base can be modified by atleast one of translation of the rotor relative to the boom; pivoting ofthe boom relative to the base; translation of the boom relative to thebase. The first rotor and the second rotor are coupled so the firstrotor and the second rotor can be repositioned in coordinated movementrelative to the base. Flight characteristics can be modified byreconfiguration of the position of at least one rotor relative to thebase.

The foregoing summary is illustrative only and is not intended to be inany way limiting. In addition to the illustrative aspects, embodiments,and features described above, further aspects, embodiments, and featureswill become apparent by reference to the drawings and the followingdetailed description.

FIGURES

FIG. 1 is a schematic elevation view of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIG. 2 is a schematic plan view of an aircraft with reconfigurablearm/boom system according to an embodiment.

FIGS. 3A to 3D are schematic plan views of a rotor system for anaircraft according to an embodiment.

FIGS. 4A to 4C are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 5A to 5E are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 6A to 6E are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 7A to 7D are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIGS. 8A to 8F are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIGS. 9A to 9D are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIGS. 10A to 10B are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 11A to 11H are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIGS. 12A to 12C are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIGS. 13A to 13C are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIG. 14 is a schematic perspective view of an arm/boom system for arotor system for an aircraft according to an embodiment.

FIGS. 15A to 15F are schematic perspective views of an arm/boom systemfor a rotor system for an aircraft according to an embodiment.

FIGS. 16A to 16D are schematic diagrams of mechanisms for an arm/boomsystem for a rotor system for an aircraft according to variousembodiments.

FIGS. 17A to 17C are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 18A and 18B are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 19A and 19B are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 20A and 20B are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIG. 20C is a schematic plan view of an aircraft with reconfigurablearm/boom system according to an embodiment.

FIGS. 21A to 21D are schematic elevation views of a rotor system withreconfigurable arm/boom system for an aircraft according to anembodiment.

FIGS. 22A to 22C are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIGS. 23A to 23C are schematic plan views of an aircraft withreconfigurable arm/boom system according to an embodiment.

FIG. 24 is a block diagram of a computing system for an aircraft systemaccording to an embodiment.

FIG. 25 is a block diagram of an aircraft system with reconfigurablearm/boom system according to an embodiment.

FIG. 26 is a block diagram of a management system for an aircraft withreconfigurable arm/boom system according to an embodiment.

FIG. 27 is a block diagram of a status monitoring system for an aircraftwith reconfigurable arm/boom system according to an embodiment.

FIG. 28A is a block diagram of data/information sets for an aircraftsystem with reconfigurable arm/boom system according to an embodiment.

FIG. 28B is a block diagram of a data management system for aUAV/aircraft system with reconfigurable arm/boom system according to anembodiment.

FIG. 29 is a block diagram of a fleet management/operation system for afleet of UAV/aircraft with reconfigurable arm/boom system according toan embodiment.

FIG. 30 is a flow diagram for a method of operation of a system forconfiguration/reconfiguration and use of an aircraft on a missionaccording to an embodiment.

FIG. 31 is a flow diagram for a method of operation of a system forconfiguration/reconfiguration and use of an aircraft on a missionaccording to an embodiment.

FIGS. 32A and 32B are flow diagrams for a method of operation of asystem for configuration/reconfiguration and use of an aircraft on amission according to an embodiment.

FIG. 33 is a flow diagram for a method of operation of a system forconfiguration/reconfiguration and use of an aircraft on a missionaccording to an embodiment.

FIGS. 34A and 34B are flow diagrams for a method of operation of asystem for configuration/reconfiguration and use of an aircraft on amission according to an embodiment.

FIG. 35 is a flow diagram for a method of operation of a system forconfiguration/reconfiguration and use of an aircraft on a mission tocarry a payload according to an embodiment.

FIGS. 36A and 36B are flow diagrams for a method of operation of asystem for configuration/reconfiguration and use of an aircraft on amission to carry a payload according to an embodiment.

DESCRIPTION

A reconfigurable unmanned aircraft system is disclosed according toexemplary and alternative embodiments. The system comprises areconfigurable unmanned aircraft configured to operate in an airspace. Asystem and method for configuring a reconfigurable unmanned aircraft anda system and method for operation and management of a reconfigurableunmanned aircraft in an airspace are also disclosed according to anexemplary and alternative embodiments.

Referring to FIGS. 1 to 23C, a selectively reconfigurable aircraft(shown as a UAV/craft V) for unmanned flight is shown representationallyand schematically according to exemplary embodiments. According to theexemplary embodiments, the UAV/craft is reconfigurable to modify flightcharacteristics in response to operating conditions under management andcontrol of a system as indicated representationally and schematically inFIGS. 24-29. Methods of use and operation of the UAV/craft and UAV/craftsystem are shown representationally and schematically according toexemplary embodiments in FIGS. 30 to 36B.

Reconfigurable UAV/Craft—Introduction

According to exemplary embodiments shown in the FIGURES, thereconfigurable UAV/craft is an aircraft generally of a “helicopter” typewith an aircraft/space frame or base and structure such as members (e.g.arms or booms) each providing for attachment of a rotor. See FIGS. 1-2.In operation (e.g. as for a “helicopter” type aircraft) the rotorsgenerate thrust and lift to propel the aircraft (including with anypayload) under the direction of a control system; as indicated, thereconfigurable UAV/craft comprises a set of rotors to generate thrustand lift. See FIGS. 1, 2, 3A-D.

According to an exemplary embodiment, the UAV/craft may be of anysuitable type or basic form of “helicopter” used for unmanned flight andprovided (as necessary or useful) with any/all associated aircraftsystems. Representative aircraft systems are known and described, forexample, in (among other literature) patent documents such as (a) U.S.Pat. No. 8,775,013 titled “System and Method for Acoustic SignatureHealth Monitoring of Unmanned Autonomous Vehicles (UAVS)”; (b) U.S.Patent Application Publication No. 20140129059 titled “Method andApparatus for Extending the Operation of an Unmanned Aerial Vehicle”;(c) U.S. Patent Application Publication No. 2014/0263823 titled“Transformable Aerial Vehicle”; and (d) U.S. Pat. No. 7,922,115 titled“Modular Unmanned Air-Vehicle”.

According to an exemplary embodiment shown representationally andschematically in the FIGURES, the aircraft comprises a base B with arotor system providing a set of rotors R on an arm/boom system A coupledto the base. See e.g. FIGS. 1-2 and 4A-B. According to exemplary andalternative embodiments of the UAV/craft, flight characteristics of theUAV/craft can be modified by reconfiguration of the position of at leastone rotor relative to the base. See e.g. FIGS. 4A-C, 5A-E, 5A-E, 10A-B,11A-H and 13A-C.

According to an exemplary embodiment, position of a rotor relative tothe base of the UAV/craft can be modified by at least one of (1)translation of the rotor relative to the boom (e.g. FIGS. 10A, 14); (2)pivoting of the boom relative to the base (e.g. FIGS. 4B, 14); (3)translation of the boom relative to the base (e.g. FIGS. 6B, 14); (4)retraction of the boom relative to the base (e.g. FIGS. 9C, 14); (5)pivoting of the rotor relative to the boom (e.g. FIGS. 14, 15F); (6)raising the height of the boom relative to the base (e.g. FIGS. 11B,14); (7) lowering the height of the boom relative to the base (e.g.FIGS. 11D, 14); (8) rotation of the rotor relative to the boom (e.g.FIGS. 11C, 14); (9) rotation/twist of the boom relative to the base(e.g. FIG. 15E). See generally FIGS. 6A-E, 11A-H, 13A-C, 14 and 15A-F.

As indicated, movement of position of a rotor of the UAV/craft can bereferenced within a polar or Cartesian or orthogonal axis system respectto at least one of a (a) longitudinal direction or axis (x), (b)vertical direction or axis (y), or (c) lateral direction or axis (z).See e.g. FIG. 14 (indicating representative axis system orientationaccording to an exemplary embodiment).

As shown representationally and schematically according to an exemplaryembodiment, the position of a rotor relative to the base (and/orrelative to another rotor or rotors) of the UAV/craft can be modified byat least two coordinated movement/motions of the arm/boom (e.g. FIGS.12A-C). The position of a rotor relative to the base can be modified byat least one coordinated motion of the rotor and the arm/boom (e.g.FIGS. 9A-D). The coordinated motion may be substantially simultaneous orsequential (or in another manner). According to an exemplary embodiment,position of a rotor relative to the base (and/or relative to anotherrotor or rotors) of the UAV/craft can be modified by coordinatedmovement/motion of multiple rotors and/or multiple arms/booms (e.g.FIGS. 23A-C).

Reconfigurable UAV/Craft

Referring to FIGS. 1 and 2, a reconfigurable UAV/craft V (aircraft) isshown representationally and schematically according to an exemplaryembodiment. The UAV/craft comprises a body or base/frame structure shownrepresentationally and schematically as base B and a set of members orarm/frame structures (e.g. space frame constructed from a member ormembers) shown representationally and schematically as arm/boom A.According to an exemplary embodiment, the UAV/craft operates as a“helicopter” aircraft with a set of rotors each shown representationallyand schematically as rotor R that in operation generate lift and thrustto propel the UAV/craft during flight/use.

As indicated, the flight characteristics of the reconfigurable UAV/craftare provided by (among other things) the positioning/relativepositioning of each rotor in the rotor system; flight characteristics ofthe reconfigurable UAV/craft may be modified bypositioning/repositioning the rotor system of the UAV/craft; afterrepositioning the reconfigured UAV/craft may have modified flightcharacteristics (e.g. suited for a particular function/operatingconditions). See e.g. FIGS. 10A-B, 17A-C, 18A-B, 19A-B, 20A-C, 21A-D,22A-C and 23A-C.

According to an exemplary embodiment, as shown representationally andschematically in FIGS. 1 and 2, the UAV/craft V is configured to carry apayload L (e.g. in or on or under or within or attached to the base); asshown schematically in FIG. 1, payload L is located under base B ofUAV/craft V; as shown schematically in FIG. 2, payload L is located (atleast partially) within base B (e.g. in a payload/cargo compartment) ofUAV/craft V. See also FIGS. 20A-C and 21A-D (e.g. example payloadcarrying configurations for UAV/craft).

According to an exemplary embodiment, the UAV/craft may be provided inany of a wide variety of shapes and forms (including shapes/forms ofaircraft that have been used or are presently in use or may be put intouse in the future). According to any preferred embodiment, the UAV/craftis configured with a plurality of operational rotors positioned relativeto base to provide for safe/stable and efficient control/management andoperation of the UAV/craft in expected operating conditions. See e.g.FIGS. 1, 2, 4A-C, 5A-E, 6A-E, 22A-C, 23A-C, 25 and 30-36B.

According to an exemplary embodiment, as shown representationally andschematically in FIG. 2, the UAV/craft is provided in the form of atri-copter (three rotors); as shown representationally and schematicallyin FIG. 4A, the UAV/craft may be provided in the form of a quad-copter(four rotors); as shown representationally and schematically in FIG. 5A,the UAV/craft may be provided in the form of a penta-copter (fiverotors); as shown representationally and schematically in FIG. 6A, theUAV/craft may be provided in the form of a octa-copter (eight rotor).According to exemplary embodiments shown representationally andschematically, the UAV/craft may be provided and/or operated in a formof a hexa-copter (six rotors, see e.g. FIG. 22B) or septa-copter (sevenrotors, see e.g. FIG. 6B) or in any of a wide variety of other formswith additional rotors (e.g. ten rotors, twelve rotors, etc.).(According to an exemplary embodiment, the UAV/craft may be constructedwith additional rotors provided in the rotor system.) As indicated,according to any exemplary embodiment at least one of the rotors of therotor system of the reconfigurable UAV/craft will be a repositionablerotor.

According to an exemplary embodiment, the UAV/craft may be configured toperform any of a wide variety of functions including but not limited tocarrying a payload such as for parcel/item delivery,monitoring/surveillance, data transmission/communications,hobby/entertainment, advertising/marketing, etc. According to anexemplary embodiment, the UAV/craft may be provided in any of a widevariety of configurations for any of a wide variety of functions andoperated and/or controlled by any of a wide variety of systems aspresently known and used in the art or as may be known and used in theart in the future. See generally FIGS. 1, 2, 4A-6D, 21A-23C, and 24-28B.The system and method of the present application as shown and describedrepresentationally and schematically, can be adapted and implemented foruse with any such UAV/craft according to the exemplary embodiments andaccording to other/alternative embodiments.

As shown representationally and schematically according to an exemplaryembodiment in FIGS. 1-2 and FIGS. 3A through 3D, the UAV/craft comprisesa rotor system with at least one rotor assembly R. According to anexemplary embodiment, the rotor assembly/system R comprises a fan (turbofan) having a set of blades or vanes N (see FIGS. 3A-B) by delivery ofpower from a power plant (e.g. at the rotor/arm system and/or with baseB as part of an energy/power system such as shown representationally andschematically in FIG. 25) under direction of a control system for theaircraft (see FIGS. 24-28B). According to an exemplary embodiment, therotor system may be provided in any of a wide variety of forms/types andarrangements such as presently known and in use or developed in thefuture; each rotor may have any of a wide variety of number and type ofblades/vanes. As shown schematically in FIGS. 3A and 3B the rotor may beprovided with “open” blades/vanes (see FIG. 3A), or may be provided witha rim or protective structure shown as rim system M (see FIG. 3B).According to an exemplary embodiment, the rotor may have fixedblades/vanes (e.g. of a set number/design) or may have adjustableblades/vanes (e.g. embodying an arrangement adapted from U.S. Pat. No.2,473,134 titled “Adjustable Rotor Blade” (e.g. FIGS. 1-4) and U.S. Pat.No. 2,844,207 titled “Adjustable Fan Blade Assembly” (e.g. FIGS. 1-3));adjustment of the pitch/position of blades/vanes of a rotor (apart of inaddition to the tilt/attitude of a rotor) in the rotor system of theUAV/craft may provide for adjustment of flight characteristics of theUAV/craft (alone or in combination with reconfiguration of rotorposition).

Referring to FIGS. 3C and 3D, as indicated representationally andschematically a rotor may be in operation (see FIG. 3C) (indicated by acircle in broken line) or a rotor may be stopped/inoperable (see FIG.3D) (indicated by a circle in solid line); according to an exemplaryembodiment, when a rotor is in operation it is configured to generatelift and thrust to facilitate (along with each other operating rotor)propulsion so that the UAV/craft can take flight to perform a functionor mission. See generally FIGS. 30-36B.

According to an exemplary embodiment, the rotor system of the UAV/craftmay be driven by an electric motor or other type of power plant (e.g. asknown and used presently); the base of the UAV/craft may comprise thepower plant and other associated systems providing for operation of therotors according to an exemplary embodiment (see FIGS. 1, 2 and 25);associated with the power plant will be an energy/energy storage systemsuch as a battery system and/or fuel storage (and/or fuel cell, solarpanel/array, etc.); according to an alternative embodiment, theUAV/craft may comprise a hybrid energy/power system comprising at leasttwo different subsystems (e.g. fuel/electric, etc.). According to anypreferred embodiment, the UAV/craft will comprise a power/energy systemas can be used to power and control rotational speed/thrust of rotor aswell as to power and control mechanisms/subsystems used to configure theUAV/craft (e.g. position/reposition rotors/arms, etc.) and otheron-board systems (e.g. control/computing systems, data/networkcommunications, etc.).

As indicated representationally and schematically according to anexemplary embodiment shown generally in FIGS. 2 and 24-36B, the controlsystem and power plant (e.g. motor, engine, etc.) are configured tooperate the rotors of the rotor system of the UAV/craft at a speed thatfacilitates control and operation of the UAV/craft (with energy providedby an energy supply/storage such as a battery system, fuel supply,energy generation system, etc.). According to an exemplary embodiment,the UAV/craft is driven by electric motors with a battery system as theenergy storage/supply. See also FIGS. 25 and 28B.

Referring to FIGS. 1, 2, 4A-D, 5A-E and 6A-E, arrangements for areconfigurable UAV/craft are shown representationally and schematicallyaccording to exemplary embodiments. As shown representationally andschematically in FIGS. 1 and 2, aircraft V has rotors R each provided ona boom/arm A coupled to base B at (e.g. by) a mechanism shownschematically as joint P configured to allow boom A and rotor R to bepositioned and repositioned relative to base B, for example, byrotation/movement (see FIGS. 4B-C, 5B-E) and/or translation/movement(see FIGS. 6B/C/D). As indicated representationally and schematically inFIGS. 1, 2, 4A-C, 5A-E and 6A-D, according to an exemplary embodiment bythe positioning and repositioning of arms/booms A with rotors R relativeto the base B (as well as to other rotors) the UAV/craft V can beconfigured and reconfigured in a wide variety of forms (providingmodified flight characteristics for one or more functions/purposes inoperating conditions). See also FIGS. 10A-B, 11A-H, 18A-B, 19A-B, 21A-D,22A-C, 23A-C and 30-36B.

For example, as shown representationally and schematically in FIG. 4A,the UAV/craft is configured and operating as a quad-copter; as shownrepresentationally and schematically in FIGS. 4B and 4C, the UAV/craftis reconfigured by repositioning of arms/booms A and rotors R to operateas a tri-copter (e.g. with one arm/boom and rotor taken out of operationand stowed or refracted at the base).

As shown representationally and schematically in FIG. 5A, the UAV/craftis configured and operating as a penta-copter; as shownrepresentationally and schematically in FIGS. 4B and 5C, the UAV/craftis reconfigured by repositioning of arms/booms A and rotors R to operateas a quad-copter (e.g. with one arm/boom and rotor taken out ofoperation and stowed or retracted at the base); as shownrepresentationally and schematically in FIGS. 5D and 5E, the UAV/craftis reconfigured by repositioning of arms/booms A and rotors R to operateas a tri-copter (e.g. with two arms/booms and rotors taken out ofoperation and stowed or retracted at the base).

As shown representationally and schematically in FIG. 6A, the UAV/craftis configured and operating as an octa-copter; as shownrepresentationally and schematically in FIG. 6B, the UAV/craft isreconfigured by repositioning of arms/booms A and rotors R to operate asa septa-copter; as shown representationally and schematically in FIGS.6C and 6D; the UAV/craft is reconfigured by repositioning of arms/boomsA and rotors R to operate in each of two different configurations of ahexa-copter. (As shown schematically in FIG. 6E, the UAV/craft may beconfigured in a relatively compact stowed or storage configuration withall arms/booms A and rotors retracted.)

As indicated representationally and schematically according to anexemplary embodiment in FIGS. 4A-C, 5A-E and 6A-D, reconfiguration ofthe UAV/craft may comprise coordinated repositioning of both theoperational rotors and the non-operational rotors both relative to thebase and relative to other rotors. For example, as indicated in FIGS. 4Ato 4C, as the non-operational rotor is retracted (e.g. rotated at jointP) operational rotors may be repositioned (e.g. rotated at joint P) tocompensate (e.g. some or all operational rotors may be moved into aposition to provide compensatory lift/thrust, mass property balancing,etc. in the absence of lift/thrust and mass that would otherwise beprovided by the non-operational rotors before reconfiguration); asindicated in FIGS. 6A to 6B, as the non-operational rotor is retracted(e.g. translated on track T with base B), operational rotors arerepositioned (e.g. rotated at joint P) to compensate (e.g. for balanceand thrust). See also FIGS. 5A, 5B-C and 5D-E; FIGS. 6A to 6C-D. Asindicated according to an exemplary embodiment, in FIGS. 6A-E,operational rotors may also be repositioned by translation or track Tand/or rotation at joint P. (As indicated representationally andschematically in the FIGURES, movement of components of the arm/boomsystem and rotor system may be performed in an independent and/orcoordinated manner and fully and/or partially within the available rangeof motion as desire under control of a control system, see FIGS.24-36B.) In coordination with the repositioning of one or more rotors,the rotational speeds of one or more rotors may also be changed when arotor becomes inoperable. Such rotor speed adjustments may, for example,be chosen so that the net rotor torque applied to the UAV/craft remainsat or near zero despite loss of torque from the inoperable rotor. Insome situations, a UAV/craft may respond to a situation where one rotorbecomes inoperable by deliberately turning off an additional rotor;e.g., a hexa-copter which loses use of one rotor may prefer operation asa quad-copter to that as a penta-copter.

According to an exemplary embodiment as shown representationally andschematically in FIGS. 7A-D, 8A-F and 9A-D, any of a wide variety ofmechanisms and motors may be employed to position and reposition therotors of the UAV/craft. See also FIGS. 14 and 16A-D. For example,according to an exemplary embodiment as shown representationally andschematically in FIGS. 7A-D, the arm/boom system comprises a trackmechanism shown as comprising a sleeve S within which arm/boom A mayretract the rotor (see FIGS. 7A-B) and/or extend the rotor (see FIGS.7C-D) relative to the base B (e.g. for independent and/or coordinatedmovement). See also FIG. 16B.

According to an exemplary embodiment as shown representationally andschematically in FIGS. 8A-F, the arm/boom system comprises a sleeve Sfor arm/boom A to retract/extend the rotor R relative to the base B aswell as a pivot joint P at which the sleeve/arm with rotor can be raised(see FIGS. 8B-D) and lowered (see FIGS. 8E-F) relative to the base B; apivot joint J for axis X of rotor R is provided so that theorientation/attitude of the rotor R can be monitored (or controlled)relative to the base B (e.g. compare FIG. 8E and FIG. 8F). See alsoFIGS. 16A/C and 21A-D.

According to an exemplary embodiment as shown representationally andschematically in FIG. 9A-D, the arm/boom system comprises a sleeve S forarm/boom A as well as a track mechanism shown as comprising a track T inbase B for (independent and/or coordinated) movement of the arm/boomrelative to the base and a track T in arm A for (independent orcoordinated) movement of the rotor R relative to the arm. See also FIG.16B. As indicated, the arm/boom system may also be configured tofacilitate movement of the arm relative to the sleeve (e.g. translationas indicated in FIGS. 7A-D) as well as other movements and combinationsof movements to reposition the rotor.

Referring to FIGS. 10A-B, a UAV/craft configured as a tri-copter isshown according to an exemplary embodiment representationally andschematically, with the arm/boom system with sleeve S so that the rotorscan be extended (see FIG. 10A) or retracted (see FIG. 10B) relative tothe base. Referring to FIGS. 11A-H, a UAV/craft is shown according to anexemplary embodiment representationally and schematically with thearm/boom system using pivot joint P at the base/arm interface and pivotjoint J at the arm/rotor interface to indicate example configurationsand reconfigurations of the UAV/craft (e.g. of the arm/rotor relative tothe base). As indicated representationally and schematically in FIGS.12A-C and FIGS. 13A-C, according to an exemplary embodiment anon-operational rotor may be retracted toward the base (see FIGS. 12Band 13B) and/or rotated within/into the base (see FIGS. 12C and 13C).

As indicated according to an exemplary embodiment, by combinations ofknown/available mechanism (including as shown representationally andschematically in FIGS. 16A-D) and movements (including as shownrepresentationally and schematically in the FIGURES) of any of a widevariety of configurations and reconfigurations of the arm/boom systemand rotor system and UAV/craft may be facilitated (including as shownrepresentationally and schematically in the FIGURES); according to anexemplary embodiment, configurations may utilize/operate all availablerotors (see e.g. FIGS. 10A-B) and/or configuration may utilize/operatecertain available rotors while not operating other rotors (see e.g.FIGS. 4A-D, 5A-E and 6A-D). According to any preferred embodiment, thereconfigurable UAV/craft may be configured by positioning/repositioningof the rotor system to provide any of a wide range of flightcharacteristics/performance as intended or useful for operatingconditions.

As indicated representationally and schematically in the FIGS. 6E and10B, some or all components of the rotor system of a UAV/craft may beretracted into the base to reduce the overall size and risk of damage toextended components such as for storage and transport of the UAV/craft.See also FIGS. 6D, 7A, 10A and 21A-C. As shown schematically in FIG. 6E,when the UAV/craft is not in use all rotors may be retracted to put theUAV/craft in a compact form for storage.

UAV/Craft—Robotic Arm Mechanism

As indicated representationally and schematically according to anexemplary embodiment, in FIGS. 14 and 15A-F, the space frame/base of theUAV/craft may be configured so that the arm/boom system for a rotor maycomprise a robotic arm mechanism to position/reposition the rotor toconfigure/reconfigure the UAV/craft. Robotic arm systems/mechanisms ofknown/present configurations and arrangements may be adapted andconstructed for use with the UAV/craft according to exemplary and otheralternative embodiments, see for example systems such as U.S. Pat. No.6,431,019 titled “Low Cost, High-Strength Robotic Arm” (e.g. FIG. 1).See also FIG. 16D (schematic representation of mechanical arm segment).

As indicated representationally and schematically, the arm/boom systemimplemented using a robotic arm mechanism will provide a flexiblemulti-axis system for rigidly positioning and repositioning a rotorrelative to the base of the UAV/craft. See e.g. FIGS. 14 and 16D. Asshown schematically in FIG. 14, the arm/boom system A comprises a baseassembly 210 to be attached to the base B of the UAV/craft and aboom/arm assembly 220 coupled to the base assembly 210 at an interface216 (shown as a joint or junction); the rotor R is installed on anarm/axis assembly 230 coupled to the boom/arm assembly 220 at aninterface 226 (shown as a joint or junction). The base assembly 210comprises a base sleeve 212 (attached to base B) with an arm segment 214(coupled to interface 216) that can be extended and/or retracted withinthe base sleeve 212 (e.g. to lower/raise the rotor see FIGS. 14 and15A). The boom/arm assembly 220 comprises a base sleeve 222 (coupled tointerface 216) with an arm segment 224 (coupled to interface 226) thatcan be extended and retracted within the base sleeve 222 (e.g. toextend/retract the rotor see FIGS. 14 and 15D). The interface 216provides for rotation of the boom/arm assembly 220 along each of threeaxes (e.g. as indicated schematically in FIGS. 14 and 15B, 15C and 15E);the interface 226 provides for rotational positioning of the rotor (e.g.using a ball joint as indicated schematically in FIGS. 14 and 15F). Seealso FIGS. 16A/C (example representation of mechanisms).

As indicated representationally and schematically according to anexemplary embodiment, the arm/boom system implemented with a robotic armprovides for multi-dimensional movement and positioning of the rotorrelative to the base, including translation of the rotor in an in/outorientation (X axis) (FIG. 15D), translation of the rotor in an up/downorientation (Y axis) (FIG. 15A), rotation of the rotor in the plane ofthe base (about the Y axis) (FIG. 15B), rotation of the rotor transverseto the base (about the Z axis) (FIG. 15C), rotation/twisting of therotor (about the X axis) (FIG. 15E), rotation/orientation of the rotorrelative to the arm (FIG. 15F). (As indicated, movement of components ofthe arm/boom system and rotor system may be coordinated and/orindependent and/or in a sequence.)

According to other exemplary embodiments, other forms of roboticarms/mechanisms may be employed for the rotor system of thereconfigurable UAV/craft.

UAV/Craft—Example Mechanisms

Referring to FIGS. 16A-D, example mechanisms that may be employed in thearm/boom system of the UAV/craft according to an exemplary embodiment,are shown representationally and schematically. As indicated any of awide variety of suitable/other mechanisms may be adapted/used inexemplary embodiments of the system, including the mechanismsspecifically shown (e.g. as joint/interface mechanism J/P, track/sleevemechanism T/S) and other known/present mechanisms and/orcommercially-available systems/mechanisms.

Referring to FIG. 16A, a joint/interface mechanism (e.g. as indicated inFIGS. 7A-D, 8A-F, 14, 21A-D, etc.) is shown representationally andschematically of a type disclosed in U.S. Pat. No. 6,238,124 titled“Locking Joint Mechanism” (e.g. FIGS. 1, 3, 4, 20-23, 38A-B). See alsoU.S. Pat. No. 4,890,713 titled “Pan and Tilt Motor for SurveillanceCamera” (e.g. FIGS. 1-3). Referring to FIG. 16B, a track/sleevemechanism (e.g. as indicated in FIGS. 6A-D, 7A-D, 8A-F, 9A-D, 22A-C,etc.) is shown representationally and schematically of a type disclosedin U.S. Pat. No. 8,226,063 titled “Power Seat Track Drive Assembly”(e.g. FIGS. 2, 7, 8). See also U.S. Pat. No. 8,534,147 titled“Electromotive Linear Drive” (e.g. FIG. 1) and U.S. Pat. No. 4,614,128titled “Linear Drive Device with Two Motors” (e.g. FIGS. 2, 4, 5).Referring to FIG. 16C, a joint/interface mechanism (e.g. as indicated inFIGS. 7A-D, 8A-F, 21A-D, etc.) is shown representationally andschematically of a type disclosed in U.S. Pat. No. 5,409,269 titled“Ball Joint Mechanism” (e.g. FIGS. 1, 2, 4) and U.S. Pat. No. 6,101,889titled “Ball Screw and Nut Linear Actuator Assemblies and Methods ofConstructing and Operating Them” (e.g. FIGS. 1, 2, 5, 7). Referring toFIG. 16D, a flexible arm mechanism of a type that may be used for thearm/boom system is shown representationally and schematically of a typedisclosed in U.S. Pat. No. 6,431,019 titled “Low Cost, High-StrengthRobotic Arm” (e.g. FIG. 1). (According to alternative and otherexemplary embodiments, other mechanisms may be adapted and used for therotor/arm system for the UAV/craft.)

According to any exemplary embodiment, the joint/interface mechanism Jand track/sleeve mechanism T indicated in FIGS. 16A-D could be used toimplement the joint/interface mechanisms J/P and track/sleeve mechanismsT/S indicated in other FIGURES; as indicated, according to thevarious/other exemplary and alternative embodiments, any of a widevariety of other known and/or suitable mechanisms (e.g. with associatedcontrol/drive systems, motors, linkages, couplings, gearing, etc.) mayused to implement the functionality of the reconfigurable UAV/craftsystem.

UAV/Craft—Spatial/Geometric Arrangement of Rotors

As indicated according to any exemplary embodiment, the arm/boom systemfor the rotor system is configured to configure and reconfigure therotor system in a geometric and spatial arrangement (e.g. in athree-dimensional space but in any event at least a two-dimensionalplane).

As indicated representationally and schematically in FIGS. 17A-Caccording to an exemplary embodiment for a reconfigurable UAV/craft witha quad-copter arrangement, configuration relative positions of rotorsmay be set in a spatial/geometric arrangement (in two and threedimensions) for functional purposes intended to achieve desired flightcharacteristics in or for operating conditions of the UAV/craft (e.g. toperform functions on a mission). For example, as shown schematically inFIG. 17A, a generally symmetrical arrangement of rotors may be providedto improve stability (e.g. such as for ascent/lift-off anddescent/landing) for the UAV/craft. The rotors (in plan view) are in agenerally “square” configuration (e.g. W_(a)=W_(b)=L_(a)=L_(b)). Asshown schematically in FIG. 17B, an arrangement of rotors may beprovided to adjust the aerodynamic profile of the UAV/craft (e.g. suchas to reduce drag in flight). The rotors (in plan view) are generally ina rectangular/non-square configuration (e.g. W_(m)=W_(n) and L_(m)=L_(n)and W_(m)<L_(m) and W_(n)<L_(n)); the profile at the UAV/craft as givenby the rotor arrangement is narrowed along the direction of forwardtravel. As shown schematically in FIG. 17C, an arrangement of rotors maybe provided to adjust the aerodynamic profile of the UAV/craft (e.g.intended to compensate for a cross-wind). The rotors (in plan view) arein a trapezoidal configuration (e.g. W_(x)=W_(y) and L_(x)>L_(y)); theprofile of the UAV/craft as given by the rotor arrangement is narrowedat the side facing an external force (e.g. cross-wind).

Referring to FIG. 21A, the reconfigurable UAV/craft is carrying asymmetrical payload that retains the center of mass of the UAV/craftgenerally in a central location as shown schematically with acorresponding symmetrical rotor configuration; rotor configuration isset at an arm/boom length to the frame/base of L_(a)/L_(b) (L_(a)=L_(b))and angle of an arm/boom relative to base is set at A_(a)/A_(b)(A_(a)=A_(b)). In FIG. 21B, the reconfigurable UAV/craft is carrying asymmetrical payload indicated schematically as having a relativelysubstantial mass (in comparison to the mass indicated in FIG. 21A) witha corresponding reconfiguration of the UAV/craft that is symmetricalwith a reduction of the lateral distance between the rotors; rotorconfiguration is set at an arm/boom length to the frame/base of L_(az)and L_(bz) (L_(az)=L_(bz)) and angle of arm/boom relative to base is setat A_(az) and A_(bz) (A_(az)=A_(bz)); as noted the angle of arm/boomrelative to base has increased.

In FIGS. 21C-D, the UAV/craft is carrying a payload that is asymmetricaland the corresponding rotor configuration of the UAV/craft isasymmetrical in an effort to compensate for the off-center location ofthe center of mass of the loaded UAV/craft. As indicated schematically,the rotor position may be reconfigured by extending/retracting and/oradjusting the angle of the arm/boom relative to the base/frame (andpayload); for example in FIG. 21C, angle of one arm/boom A_(az) relativeto the base/frame is less than the angle of the other arm/boom A_(bx)relative to the base/frame; in FIG. 21D, the length of one arm/boomL_(ay) relative to the base/frame is larger than the length of the otherarm/boom L_(by) relative to the base/frame.

As indicated according to an exemplary embodiment, other arrangement ofrotors and other intended purposes may be considered in thedetermination of configurations and operation of the reconfigurableUAV/craft. According to an exemplary embodiment the control system (seeFIGS. 24-28B), will control the configuration/reconfiguration andpositioning/repositioning of the rotor system to desiredgeometric/spatial relationships for the desired flight characteristicsof the reconfigurable UAV/craft.

Operation/Management—Rotor Speed Control

According to an exemplary embodiment, the rotor system of thereconfigurable UAV/craft is configured to provide a variable amount ofthrust (e.g. with variable speed control of one or more rotors underdirection of a control system, see FIGS. 24-28B). The flightcharacteristics of the reconfigurable UAV/craft can be modified(separately or in addition to by repositioning of the rotor system) bycontrol/adjustment of rotor speed.

According to an exemplary embodiment, each rotor has a desired operatingrange of rotor rotational speed for operation; the operating rangecomprises a low threshold speed and a high threshold speed (e.g.determined by design or conditions). The low speed is a designed minimumspeed and the high speed is a designed maximum speed. According to anexemplary embodiment, a threshold rotor speed may be based on at leastone of energy efficiency or stability performance.

According to an exemplary embodiment, the control system (e.g. mastercontrol system) of the reconfigurable UAV/craft may comprise a firstsubsystem (e.g. operation control) for changes in rotor rotational speedand a second subsystem (e.g. configuration control) forconfiguration/reconfiguration of the arm/boom system and/or rotorsystem; if a change in flight characteristics is desired (e.g. due tochanges in operating conditions) the control system initially will seekto use operation control to change in rotor rotational speed (e.g. as a“quick” response from the system); the control system then will seek touse reconfiguration control to change rotor position (e.g. a “slower”response from the system) to modify flight characteristics of thereconfigurable UAV/craft. See e.g. FIGS. 25 and 34A-B.

In operation according to an exemplary embodiment, the UAV/craftresponding to a change in operation/flight conditions with a change offlight characteristics may seek to change rotor speed; but eventually(e.g. if required speed changes are large and/or beyond anoff-design-point rotor speed threshold) response to the operating/flightconditions may require a reconfiguration of the UAV/craft byrepositioning of the rotor system. According to an exemplary embodiment,the system will seek to operate all rotors efficiently (i.e., rotors aremost efficient at a given design speed) to a threshold level using rotorspeed control; beyond the threshold level change allowing rotor speedcontrol alone the system will reconfigure the rotor system (e.g. one ormore rotors or arms/booms); according to an exemplary embodiment, afteror in conjunction with reconfiguration the system may adjust rotorspeeds (e.g. operate rotors at or within the design speed/threshold). Asindicated, coordinated control of rotor speed with configuration ofrotor position facilitates a wider range of available flightcharacteristics and operating performance (e.g. balancing/reducingloads/operational intensity/speed, wear, etc.); according to anypreferred embodiment, the control system of the reconfigurable UAV/craftis able to operate the rotor system at regulated speeds within thethreshold operating range (e.g. within restrictions but achievingdesired lift/thrust) under a wide range of operating conditions/demandsby coordinating rotor speed control with rotor position configurationfor the UAV/craft.

UAV/Craft—Control/Computing Systems

According to an exemplary embodiment as shown representationally andschematically in FIGS. 24-28B, the system and method can be implementedusing a computing system programmed or otherwise configured to managethe operations, functions and associated data/network communications.Referring to FIGS. 24-28B according to an exemplary embodiment shownrepresentationally and schematically, a control system is provided tomanage, configure and operate the UAV/craft.

Referring to FIG. 24, a computing system is shown schematicallyaccording to an exemplary embodiment, to comprise a processor andmemory/storage for data/programs as well as network/communicationinterfaces and input/output (I/O) system (e.g. allowing interactionthrough a user interface, etc.).

As shown schematically according to an exemplary embodiment in FIG. 25,the UAV/craft system comprises multiple functional subsystems (which maybe independent or combined in implementation) including a master controlsystem, monitoring/communication system, flight/operation controlsystem, configuration control system, energy/power control system (andother associated subsystems).

As shown schematically according to an exemplary embodiment in FIG. 26,functional modules may be associated with a computing system to manageand operate the UAV/craft, including for the power plant/energy storagesystems (e.g. motors and/or engines, battery and/or fuel systems, etc.),administration, status/condition monitoring, mission control,configuration management, etc.

Systems/modules M (e.g. individually and/or collectively) for control,operation, management, administration, data/networking, communications,telemetry, power, energy, configuration, monitoring, etc. that may beinstalled on or associated with the UAV/craft according to an exemplaryembodiment are indicated representationally and schematically in FIG. 1.See also FIGS. 24-26 and 28B.

As shown schematically according to an exemplary embodiment in FIG. 27,UAV/craft status monitoring comprises management of the configurationand mission (e.g. plan/route) for the UAV/craft as well as monitoring ofconfiguration options, conditions (e.g. operating conditions),capability/mode of operation, state/status of systems, etc.; monitoringmay comprise tracking of operation history (e.g. data available toassess status/state of health/operating condition such as to facilitatepredictive/advance identification of potential system issues, e.g. rotorfailures/malfunctions, etc.).

As shown schematically according to an exemplary embodiment in FIGS.28A-B, data and data management for the system and method may comprisecollection/monitoring and use of data from a variety of data sources(e.g. internal/network or external/internet/etc.) related to a varietyof UAV/craft systems and functions, including conditions, UAV profile,configuration, status, instrumentation, energy/power systems, etc.

Flight Characteristics/Operating Conditions

According to an exemplary embodiment, the reconfigurable UAV/craft canbe reconfigured to modify the flight characteristics in response to anyof a wide range of operating conditions that are anticipated orencountered in operation of the UAV/craft on a mission (e.g. performinga function on a flight/route in an airspace).

The flight characteristics of the UAV/craft may comprise at least one ofaerodynamic profile, maneuverability, available thrust (e.g. totalavailable thrust), available lift (e.g. total available lift), energyconsumption, energy efficiency, mass, center of gravity, massproperties, center of mass, balance, stability, controllability,maneuverability, control axes, maximum relative ground velocity, maximumrelative air speed, ascent rate, descent rate, sink rate, flightaltitude, aerodynamic drag, number of operational rotors, control systemtype, equipment status, etc. (or any other characteristic affecting theflight/performance of the UAV/craft).

According to exemplary embodiments, the flight characteristics of thereconfigurable UAV/craft can be modified by at least one of (a) changingrotation speed of at least one rotor or (b) changingposition/configuration of at least one rotor of the rotor systemrelative to the base or another rotor or (c) changing pitch ofblades/vanes of at least one rotor of the rotor system. Referring morespecifically to the FIGURES, according to an exemplary embodiment,flight characteristics of the reconfigurable UAV/craft can be modifiedby at least (1) translation of the rotor along the boom; (2) pivoting ofthe boom relative to the base; (3) extension of the boom and rotorrelative to the base; (4) retraction of the boom relative to the base;(5) pivoting of the rotor relative to the boom; (6) raising the heightof the boom relative to the base; (7) lowering the height of the boomrelative to the base; (8) rotation of a rotor relative to the base; (9)rotational twist of the boom relative to the base; (10) changing spacingof the rotor relative to another rotor; (11) changing incline of therotor; (12) changing horizontal position of the rotor relative to thebase; (13) changing the vertical position of the rotor relative to thebase; (14) moving the rotor inward relative to the base; (15) moving therotor outward relative to the base; (16) tilting the rotor; (17)adjusting the pitch of vanes of a rotor; (18) changing the rotationspeed of the rotor; (19) changing the rotor thrust; (20) disabling therotor. As indicated, according to an exemplary embodiment the controlsystem of the reconfigurable UAV/craft may command one and/or variousand/or multiple actions in an effort to modify flight characteristics ofthe reconfigurable UAV/craft, before or during operation and/or in asequential and/or coordinated manner.

According to an exemplary embodiment, the flight characteristics of thereconfigurable UAV/craft will be modified before a mission (e.g. inanticipation of the operating conditions); the flight characteristics ofthe reconfigurable UAV/craft may also be modified during a mission (e.g.in anticipation of changed operating conditions, in response toencountered operating conditions for a mission, etc.).

The operating conditions for a mission by aircraft may comprise at leastone of operability of each rotor, energy storage capacity, remainingenergy storage, payload profile, payload mass, payload type, payloadshape, payload size, payload changes, route, altitude, traffic, weatherconditions, weather effects, wind velocity, wind direction, distance ofmission, remaining distance of mission, time for mission, remaining timefor mission, fuel storage capacity, remaining fuel, energy storagecapacity, remaining stored energy, etc. (or any other of the variousconditions that the UAV/craft will encounter during a flight/mission).

According to the exemplary embodiments, the reconfigurable UAV/craftwill be designed/constructed and can be configured and/or to bereconfigured to operate efficiently in a wide range of operatingconditions. See generally FIGS. 4A-C, 5A-D, 6A-E, 10A-B, 11A-H, 13A-C,17A-C, 18A-B, 19A-B, 20A-C, 21A-D, 22A-C and 23A-C (schematicrepresentation or example forms/configurations).

Configuration/Reconfiguration for Mission/Duty

According to an exemplary embodiment, the reconfigurable UAV/craft willbe capable of configuration and reconfiguration for any of a widevariety of functions/duties on a wide variety of routes to perform awide variety of missions/mission segments. See e.g. FIGS. 30-31, 32A-B.For example, as indicated according to an exemplary embodiment, theUAV/craft will be able to be configured and reconfigured to performmissions and mission segments that involve pick-up and delivery ofpayload of a wide variety of types, mass/weight, size, shape, etc. Seee.g. FIGS. 1-2, 18A-B, 19A-B, 20A-C, 21A-D, 22A-C, 23A-C and 30-36B.(Payload may comprise items for delivery such as parcels/packages and/oritems for use such as on-board cameras/sensors, etc.)

As indicated in FIGS. 32A-32B and 36A-36B, the UAV/craft may beconfigured/reconfigured before and during a mission that may comprisemultiple mission segments. As shown schematically according to anexemplary embodiment in FIG. 32B, the UAV/craft may be employed toperform a multi-segment mission (each mission segment indicated A/B/C/D)in a corresponding set of configurations/reconfigurations (eachconfiguration indicated A/B/C/D). For example, mission segment A may beto carry a sizable payload with the UAV/craft in configuration A (seee.g. FIG. 22A) (octa-copter); mission segment B may be to travel withoutpayload with the UAV/craft being reconfigured to configuration B (seee.g. FIG. 6A) (octa-copter without payload) to a pick-up location(and/or to perform surveillance or monitoring while in transit using anon-board camera/video system); mission segment C may be to pick up atwo-component payload and carry the payload to a location with theUAV/craft being reconfigured to configuration C (see e.g. FIG. 22B)(hexa-copter); mission segment D may be to return to a base station withthe UAV/craft being reconfigured to configuration D (see e.g. FIG. 22C)(quad-copter) (and/or with the UAV/craft to provide wireless datacommunications while in transit using an on-board datacommunications/network system indicated as payload component A).

According to an exemplary embodiment as shown representationally andschematically, the same reconfigurable UAV/craft may beconfigured/reconfigured to carry a variety of types of payload (e.g.payload components) by positioning/deployment of the rotor system so asto configure the UAV/craft with the capacity to carry the payload (e.g.to perform the duties of the mission/mission segment); to carryheaver/bulkier payload (or otherwise for “heavy-duty” mission segments),the UAV/craft may deploy a larger number of rotors of the rotor systemand/or may position the rotors to support/balance the heavy-duty payload(see e.g. FIGS. 21B and 22A); to carry lighter payload (or otherwise for“light-duty” mission segments), the UAV/craft may deploy a lesser numberof rotors of the rotor system and/or may position the rotors tosupport/balance the light-duty payload (see e.g. FIGS. 21A and 22C).

According to exemplary and alternative embodiments, the same UAV/craftis able by configuration/reconfiguration to operate as a multi-functionaircraft having different flight/performance characteristics (e.g.carrying capacity, efficiency, etc.) and able to adapt to (or be adaptedfor) variations in operating conditions (e.g. rotor operability,wind/weather, etc.): (a) according to an exemplary embodiment, the rotorposition configuration of the UAV/craft may be modified and/or thenumber of operational rotors may be modified; (b) according to anexemplary embodiment, the UAV/craft may by variations of rotor speed(e.g. control of thrust at a rotor) be able to adapt to variations inoperating conditions or performance demands/needs; (c) according to analternative embodiment, the rotor system of the UAV/craft may compriserotors that have adjustable vanes/blades so that further adaptations areable to be made in response to operating conditions and/or performanceneeds/demands; (d) according to another alternative embodiment, thecarrying capacity of a UAV/craft system may be enhanced byjoining/latching two or more UAV/craft together (e.g. using conventionaland/or other fastening/coupling techniques and structures) so that twoUAV/craft function as a single aircraft with enhanced lift capabilitythat may be used to transport larger payload than a single UAV/craftwould be advised to carry.

According to an exemplary embodiment, the reconfiguration of the rotorsystem of the reconfigurable UAV/craft for a mission/purpose can bedirected by a control system (e.g. a control system onboard theUAV/craft or remote from the craft and connected by a communication/datalink) with rotors/booms capable of being independently positioned (e.g.and with rotor position monitored by a monitoring system/sensor). Seee.g. FIGS. 1, 6A-E, 14, 24-28B (e.g. system for control of motorsystem/mechanisms for reconfiguration). According to an alternativeembodiment, the relative positioning of rotors in the rotor system maybe constrained (e.g. coupled by a control system/program and/or by amechanism/linkage) so that two or more of the rotors/booms move as acoordinated unit; a coupling (e.g. mechanism, gear system, linkage,frame, member, motor/drive system, etc.) may be configured to retainduring movement/reconfiguration of the relative position of two or moreof the rotors and/or the relative position of the booms on which therotors are mounted (e.g. a coordinated system for control of motorsystem/mechanisms for reconfiguration). See e.g. FIGS. 1, 5A-E, 14,17A-C, 24-28B. According to any preferred embodiment, the configurationsystem of the UAV/craft will be capable of repositioning one or morerotors of the rotor system in a manner that will retain airworthiness(among other flight characteristics), including but not limited to byimposing limited options/system constraints onrepositioning/reconfiguration of the rotor system/boom. See e.g. FIGS.25, 26 and 28B. As indicated, according to an exemplary embodiment, thereconfigurable UAV/craft may be configured so that the rotor system canbe reconfigured at any of a variety of times/situations including beforeand during a mission.

Payload Considerations

According to an exemplary embodiment, the reconfigurable UAV/craft isconfigured to carry a payload (e.g. equipment, items forpick-up/delivery, etc.). As shown representationally and schematicallyin FIGS. 1, 2 and 18A-23C according to an exemplary embodiment, payloadcan be carried by the UAV/craft in variety of arrangements (e.g. in, on,under, within, attached, mounted, suspended, stowed, etc. with respectto the base/body). According to an exemplary embodiment, the UAV/craftcan be adapted to carry payload of any presently known type/form in anypresently known arrangement. According to an exemplary embodiment thespace frame and/or base of the UAV/craft can be adapted for thetype/form of payload to be carried. (Referring to FIGS. 1, 2 and 20A-Cand 21A-D according to exemplary embodiments, the UAV/craft isconfigured to be loaded with/to carry a variety of forms of payload invarious different configurations.)

The payload may comprise equipment such as a monitoring system, acommunication system, a surveillance system, a data gathering system, orany other types of items/articles. As indicated, the payload willcomprise properties including mass properties such as mass, shape,moment of inertia, center of mass, etc. as well as shape and dimension(e.g. size). The payload may have other characteristics such asfragility, volatility, thermal/temperature restrictions,force/acceleration restrictions, etc. The payload may have anasymmetrical/irregular or eccentric/unbalanced shape or packaging. Thepayload may have multiple components (e.g. multiple payload sections).See e.g. FIGS. 22A-C and 23A-C. According to an exemplary embodiment,the payload may comprise at least one of an article to be delivered (seeFIGS. 20A-C) or a plurality of articles to be delivered (see FIGS. 22A-Cand 23A-C).

According to an exemplary embodiment, the reconfigurable UAV/craft maycomprise a monitoring system to monitor the status/conditions aircraftsystems/subsystems including the payload; the monitoring system maycomprise a device or sensor to monitor the condition of the payload(e.g. integrity and placement of the payload).

According to an exemplary embodiment shown representationally andschematically, the payload may be supported using the base in a varietyof arrangements (see FIGS. 20A-C and 21A-D); the payload may becontained within the base (see FIG. 20B); the payload may be externallymounted to the base (see FIGS. 20A and 21A-D). As indicated, theform/shape of the payload as well as the mass properties/moment of thepayload and the attachment method of the payload each may affect theflight characteristics and operating conditions of the UAV/craft withpayload.

According to an exemplary embodiment, the flight characteristics of thereconfigurable UAV/craft can be modified at the time a payload isassociated (e.g. before a mission); the payload properties includingmass as carried by the UAV/craft can be evaluated/assessed; and theposition of at least one rotor can be modified to compensate for theposition/properties of the mass of the payload relative to the base(e.g. mass, center of mass, moment arm/force, etc.). According to anexemplary embodiment, position of at least one rotor of the rotor systemcan be repositioned relative to the base to compensate for theproperties/mass of the payload as carried by the UAV/craft. See FIGS.20A-C, 21A-D, 22A-C and 23A-C. According to any preferred embodiment,the rotor system of the reconfigurable UAV/craft with payload may beconfigured in a compact maneuverable configuration that minimizes drageffects and facilitates control/control movements of UAV/craft forstable and efficient operation on a mission (in consideration ofstatic/dynamic effects of the payload as carried or as may occur inflight, including lagging/shifting/moments/forces, etc.).

Referring specifically to FIGS. 18A-B, 19A-B, 20A-B, 21A-B, 21A-D, 22A-Cand 23A-C, according to an exemplary embodiment as shownrepresentationally and schematically, the rotor position andconfiguration of the UAV/craft can be modified to carry payload in avariety of configurations and situations/operating conditions and toadapt flight characteristics in response to payloadconfigurations/conditions.

As indicated representationally and schematically according to anexemplary embodiment, configuration/reconfiguration of thereconfigurable UAV/craft in response to properties of payload and otheroperating conditions may be implemented for any of a variety ofpurposes/intent as suitable within the operational parameters of theUAV/craft (see e.g. FIGS. 30-36B); configuration/reconfiguration of thereconfigurable UAV/craft may be implemented prior to a mission toachieve energy efficiency and/or to reduce aerodynamic drag and/or toreduce travel time and/or otherwise to improve performance on themission with payload; reconfiguration of the reconfigurable UAV/craftmay be implemented during a mission in response to weather conditionsand/or a detected malfunction of a rotor/equipment and or totraffic/routing and/or other operating conditions anticipated orencountered by the UAV/craft on the mission. Before and during themission, considerations relating to flight characteristics such asfuel/energy efficiency, enhanced performance/speed, properties of thepayload (e.g. weight, center of mass, inertia effects,handling/fragility, etc.), safety/precautions, etc. may be the basis forconfiguration/reconfiguration of the UAV/craft with payload.

As shown schematically in FIGS. 18A-B, the UAV/craft is carrying payloadL (e.g. in/on/under base B) and is configured to operate (beforereconfiguration) as a quad-copter (FIG. 18A) or to operate (afterreconfiguration) as a tri-copter (FIG. 18B). As shown in FIG. 18B, onerotor is non-operational and the UAV/craft is operating with threerotors in service (and repositioned) to compensate to carry payload L;as shown in FIG. 18A the same type/form of UAV/craft is operating withfour rotors in service. As shown schematically according to an exemplaryembodiment in FIGS. 19A-B, the UAV/craft is carrying payload L and isconfigured to operate as a penta-copter (FIG. 19A) or to operate as aquad-copter (FIG. 19B) (e.g. by taking one rotor out ofservice/operation and repositioning other rotors to compensate asnecessary/useful for the purpose/intent).

As shown representationally and schematically according to an exemplaryembodiment in FIGS. 20A-C, the UAV/craft is carrying a payload L that isoff-center/asymmetrical with respect to the body/base B (see e.g. FIGS.20A-B); intended to compensate for the mass property effect of theoff-center payload, the rotors of the UAV/craft have been repositionedto reconfigure the UAV/craft to carry the payload notwithstanding theasymmetry. As shown schematically, two rotors have been extended (e.g.using a sleeve/arm mechanism, see also FIGS. 7A-D) so that the relativeposition of the payload is more generally symmetrical with respect tothe set of rotors of the UAV/craft.

Referring to FIGS. 21A-D, various other payload/base arrangements areshown representationally and schematically according to an exemplaryembodiment with corresponding configurations of the rotors at theUAV/craft intended to compensate for mass property/other effects of thepayload. In FIG. 21A, a symmetrical payload that retains the center ofmass of the UAV/craft generally in a central location is shownschematically with a corresponding symmetrical rotor configuration;rotor configuration is set at an arm/boom length to the frame/base ofL_(a)/L_(b) (L_(a)=L_(b)) and angle of an arm/boom relative to base isset at A_(a)/A_(b) (A_(a)=A_(b)). In FIG. 21B, a symmetrical payloadindicated schematically as having a relatively substantial mass (incomparison to the mass indicated in FIG. 21A) results in areconfiguration of the UAV/craft that is symmetrical with a reduction ofthe lateral distance between the rotors; rotor configuration is set atan arm/boom length to the frame/base of L_(az) and L_(bz)(L_(az)=L_(bz)) and angle of arm/boom relative to base is set at A_(az)and A_(bz) (A_(az)=A_(bz)); as noted the angle of arm/boom relative tobase has increased. In FIGS. 21C-D, the payload is asymmetrical and thecorresponding rotor configuration of the UAV/craft is asymmetrical in aneffort to compensate for the off-center location of the center of massof the loaded UAV/craft. As indicated schematically, the rotor positionmay be reconfigured by extending/retracting and/or adjusting the angleof the arm/boom relative to the base/frame (and payload); for example inFIG. 21C, angle of one arm/boom A_(az) relative to the base/frame isless than the angle of the other arm/boom A_(bx) relative to thebase/frame; in FIG. 21D, the length of one arm/boom L_(ay) relative tothe base/frame is larger than the length of the other arm/boom L_(by)relative to the base/frame.

Referring to FIGS. 22A-C and FIGS. 23A-C, according to an exemplaryembodiment shown representationally and schematically, the UAV/craft iscarrying a multi-component payload L with components A/B/C (e.g. payloadsegments). According to an exemplary embodiment, the mission of theUAV/craft is to make successive deliveries of each component A/B/C ofpayload L as separate locations. At the start of the mission theUAV/craft is configured as an octa-copter with the complete payload Lcomprising components A/B/C (see FIGS. 22A and 23A); after the firstdelivery (of component C) the payload comprises components A/B (atreduced mass) and the UAV/craft is configured as a hexa-copter (seeFIGS. 22B and 23B); after the second delivery (of component B) thepayload comprises component A (of further reduced mass) and theUAV/craft is configured as a quad-copter (see FIGS. 22C and 23C). Asindicated representationally and schematically, the UAV/craft of FIGS.22A-C is reconfigured by a different mechanism (e.g. rotors orarms/booms retracting/extending by translation in tracks) than theUAV/craft of FIGS. 23A-C (e.g. rotors or arms/booms retracting/extendingby rotation into/within base).

As indicated representationally and schematically according to anexemplary embodiment, the non-operational rotors may be retracted in thebase as to reduce drag effects and enhance the aerodynamicprofile/performance of the UAV/craft with payload; according to anexemplary embodiment the energy efficiency and/or performance of theUAV/craft may be improved (e.g. in a corresponding manner) as the massof the payload is reduced (e.g. as components of the payload aredelivered). As also indicated schematically in FIGS. 22A-C and 23A-C,repositioning of the rotors to reconfigure the UAV/craft may beperformed as a coordinated motion of multiple rotors each oncorresponding arms/booms in a sequence substantiality, simultaneously,or in a variation/combination of coordinated/sequential movements. Seee.g. FIGS. 6A-D, 11A-H, 12A-C and 13A-C.

According to the exemplary embodiments shown representationally andschematically, the reconfiguration of rotor position can be implementedto rebalance mass properties of the UAV/craft with payload, including inview of the form/shape and size/mass of the payload and the manner inwhich the payload is associated with the UAV/craft. For example, themass property effects of the payload of the UAV/craft may vary dependingupon whether the payload is supported with the base, contained withinthe base, externally mounted to the base, suspended from the base, etc.;the shape of the payload may also determine how the payload isassociated with the UAV/craft. See FIGS. 21B (payload suspended from thebase of the UAV/craft) and 21C-D (payload with irregular, eccentric,asymmetrical mass properties). The flight characteristics of thereconfigurable UAV/craft can be modified at the time a payload isassociated with the base; a subsequent reconfiguration may be intendedto compensate for shape/dimensions of a payload or to compensate formass properties of a payload; a subsequent reconfiguration may be duringa mission to rebalance mass properties after partial delivery ofpayload. According to an exemplary embodiment, as the payload having amass is carried the position of at least one rotor is modified tocompensate for the mass of the payload (including the position of themass of the payload relative to the base.

A method of configuring a reconfigurable UAV/craft for a mission tocarry a payload having a shape may comprise the steps of determining theproperties of the payload; determining the manner in which the payloadwill be coupled to the aircraft/base; determining a modifiedconfiguration for the rotor system to compensate for the shape and massof the payload relative to the base; and positioning the rotor system inorder to balance the mass of the payload relative to the craft/base.According to an embodiment, a reconfigurable UAV/craft may begin amission with a short low altitude hovering phase in which it empiricallydetermines its center of mass characteristics (e.g. offsets due topayload or fuel imbalances) and then repositions the rotor system inorder to balance the center of mass and lift loads, before continuingits ascent and mission. According to an exemplary embodiment, the systemmay respond to a shift in the payload (e.g. shift in center of gravityor mass of the payload) by reconfiguration of the rotor system tocompensate for the change the mass properties and/or to preserve orrestore/reestablish intended flight dynamics.

Location for Reconfiguration During Mission

According to an exemplary embodiment, the reconfigurable UAV/craft willinitially be configured prior to the start of a mission/flight while onthe ground at a station. The UAV/craft will initiate the flight with aflight configuration (or after transitioning from an ascentconfiguration to the flight configuration immediately after ascent, seeFIGS. 17A and 17B).

Once in operation/flight on the mission the reconfigurable UAV/craft maybe able to maintain flight stability so that reconfiguration may takeplace without landing the UAV/craft; maintaining flight stability duringreconfiguration may comprise an intermediate repositioning of rotors(e.g. to maintain mass balance in the repositioning process) and/or anoperation with intermediate rotor speed for operational rotors (e.g. tomaintain elevation/lift and stability). According to an exemplaryembodiment, the UAV/craft may be commanded by the control system tohover at a designated elevation and/or to or above locate to a specifiedlocation (e.g. for safety/precautionary purposes) duringreconfiguration. According to an exemplary embodiment, if areconfiguration is necessary or advisable during a mission/flight, theUAV/craft may be commanded or directed to land at a specified location(e.g. lot or station) for reconfiguration; after reconfiguration theUAV/craft will resume the mission/flight if operational (or may returnto a service center/station). According to a preferred embodiment, themonitoring system of the reconfigurable UAV/craft is able to providedata to inform the control system/program as to the status/condition ofthe aircraft/subsystems to facilitate a determination ofhow/where/whether reconfiguration should be performed.

Methods of Operation/Management

According to an exemplary embodiment, the reconfigurable UAV/craftsystem may be used to perform a variety of duties/functions implementedwith apparatus/systems/subsystems according to methods foroperation/management as indicated representationally and schematicallyin FIGS. 30 to 34A/B (generally) and FIGS. 35 to 36A/B (with payload).See also FIGS. 24 to 28B (system/system and data/management functions).

Referring to FIG. 30, according to an exemplary embodiment of a methodof operation/management the reconfigurable UAV/craft is configured in aninitial configuration and operated to perform a duty/mission whileoperating conditions are being monitored; if monitoring of operatingconditions indicates that reconfiguration is advisable (e.g. monitoringof acoustic data, data from stress/strain/force gauges/sensors at arotor/rotor mount, etc. indicates a potential rotor malfunction may beimminent) the UAV/craft will determine whether to reconfigure. As shown,if the UAV/craft is reconfigured (e.g. configuration is modified toadjust rotor positioning to adjust capability to the conditions or toshutdown/retract the malfunctioning/about-to-fail rotor whilerepositioning the operable rotors) the UAV/craft can complete some orall of the remaining mission segments. As indicated, according to anexemplary embodiment the method comprises use of data from data sources(e.g. on aircraft systems, network data, control/commands, operatingprograms, data communications, etc.) by the UAV/craft system inoperation, monitoring, configuration, etc. See FIGS. 24-28B (controlsystem/program implementation).

Referring to FIG. 31, a method of planning/configuring a reconfigurableUAV/craft for a mission is shown representationally and schematicallyaccording to an exemplary embodiment. The mission (including missionsegments, duty/route, etc.) is planned; forecasted/anticipatedconditions (e.g. operating conditions expected to be encountered) forthe mission are evaluated (including using data from datasources/analytics); the UAV/craft is configured for the mission(including by deployment and positioning of the rotor system) inconsideration of the mission/payload and anticipated operatingconditions, among other considerations; the UAV/craft is deployed tobegin the mission in the configuration. The operation of the UAV/craftin the configuration (including situation/conditions of operation) ismonitored; adjustment in the operation (e.g. control of rotor speed)and/or configuration (e.g. reconfiguration of rotor position) may beimplemented for the UAV/craft as necessary or advisable in the situation(e.g. under operation of a control system/program); operation of theUAV/craft is monitored in real-time as the mission is executed tocompletion. (As indicated, data may be interchanged between theUAV/craft and a base station/data sources during operation.)

Operation/Management Method—Mission Segments/Configurations

Referring to FIGS. 32A and 32B, according to a method as shownrepresentationally and schematically according to an exemplaryembodiment, a reconfigurable UAV/craft may be deployed for a (planned)mission comprising multiple mission segments (e.g. multipleseparate/discrete tasks or functions); as indicated, the reconfigurableUAV/craft may be configured and equipped and loaded initially thenreconfigured for each mission segment as the mission is executed tocompletion. See FIG. 32A (mission with segments A/B and correspondingcraft configurations A/B) and FIG. 32B (mission with segments A/B/C/Dand corresponding craft configurations A/B/C/D).

Referring to FIG. 33, the reconfigurable UAV/craft may be provided withcertain set (e.g. pre-programmed) configurations (e.g. of the rotorsystem) for certain routine/regular/other functions or operations of theUAV/craft; as indicated, the UAV/craft has an “ascend” configuration forthe rotor system (e.g. intended to optimize performance/stability as theUAV/craft ascends to take flight at a station/stop); the UAV/craft has a“descend” configuration of the rotor system (e.g. intended to optimizeor enhance performance/stability as the UAV/craft lands at astation/stop to complete a flight). As indicated, during flight (afterascent/take-off) the UAV/craft may be monitored (e.g. with data fromdata sources) and reconfigured as needed/advisable for the situation(e.g. determined by the control system/program) until the UAV/craft isto descend/land at the end of the mission; as indicated, during theflight on the mission monitoring may be regular and/or a continuous(e.g. in real-time) during operation and the UAV/craft may bereconfigured at least once or multiple times (or not at all/only atascent and descent). (According to an exemplary embodiment, theUAV/craft may be reconfigured while in flight without landing or may belanded or hovered in a location for reconfiguration to be executed.)

Operation/Management Method—Rotor Speed Adjustment and/or Rotor PositionAdjustment

Referring to FIGS. 34A and 34B, a method of operation and management ofa reconfigurable UAV/craft is shown representationally and schematicallyaccording to an exemplary embodiment. According to an exemplaryembodiment, the reconfigurable UAV/craft is configured for adjustment ofrotor speed and for modification of rotor position; operation andmanagement of the UAV/craft comprises the capability to use both rotorspeed and rotor position for flight control (e.g. for control of flightcharacteristics) of the UAV/craft. (As indicated, rotor positionmodification may comprise reconfiguration of position or pitch/attitudeof one or more rotors of the rotor system of the UAV/craft.)

As indicated in FIGS. 34A-B, in a method according to an exemplaryembodiment the reconfigurable UAV/craft is configured to ascend and tofly on the mission and is monitored during the mission; if a situationis detected during flight that under the control program/system mayrequire an adjustment/modification of flight characteristics of theUAV/craft, the determination will be made by the system as to whether anadjustment of rotor speed (to the situation) will be suitable as anadaptation for the situation to facilitate confirmed operation of theUAV/craft; if so rotor speed will be adjusted (to the situations) andflight will continue with no modification of rotor position (e.g. nochange in position of any rotor of the rotor system). If the systemdetermines that modification of rotor position is warranted, rotorposition will be modified and the UAV/craft will be reconfigured (to thesituation); a determination will be made as to whether adjustment ofrotor speed is also warranted and if so rotor speed will also beadjusted (to the situation) and flight will continue with a reconfiguredUAV/craft. The flight of the UAV/craft on the mission will continueuntil the UAV/craft is commanded to land and/or has completed themission. (If in a situation a suitable response is not possible oradvisable using adjustment of rotor speed and/or reconfiguration ofrotor position, the UAV/aircraft may be commanded to end the flight andreturn/land.) See FIG. 34A. (For example, by design or in anapplication/installation in a UAV/craft, a rotor may have an operatingspeed range that is specified; the system may be configured so that therotor is operated within the operating speed range; such range may bedetermined by the type of rotor system, power plant, etc.)

As indicated in FIG. 34B according to an exemplary embodiment, the rotorspeed of the reconfigurable UAV/craft may be restricted or limited inrange (e.g. minimum and maximum design speed) by design and/or by thecontrol system/program of the UAV/craft. As indicated, if the rotorspeed adjustment to respond to the situation would require operation ata rotor speed outside of the suitable/intended range of operation (e.g.design operating range) then the response to the situation may requirereconfiguration of the rotor position (for the situation); adjustment ofrotor speed (within the suitable/intended design/control range) may alsobe made for the reconfigured UAV/craft. See FIG. 34B. As indicatedaccording to an exemplary embodiment, operation and management of thereconfigurable UAV/craft is performed using rotor speed control androtor position configuration.

Operation/Management Method—Configuration/Reconfiguration

According to an exemplary embodiment of the reconfigurable UAV/craft asshown schematically in FIGS. 17A-C, the reconfiguration of position ofat least one rotor in the rotor system can be performed before operationof the aircraft in response to anticipated operating conditions (seeFIGS. 17B-C). According to an exemplary embodiment, the reconfigurationof position of at least one rotor can be performed before operation ofthe aircraft in response to desired flight characteristics and/or inresponse to the payload (e.g. FIGS. 21A-D).

According to an exemplary embodiment as indicated representationally andschematically in FIGS. 17A-B, a method of operating a reconfigurablemulti-rotor unmanned aircraft for flight characteristics on a mission inoperating conditions may comprise the steps of (a) configuring theaircraft in an ascent configuration with flight characteristics forascent to start a flight (e.g. FIG. 17A); (b) configuring the aircraftin a second configuration with flight characteristics for flight inoperating conditions (e.g. FIG. 17B); and (c) configuring the aircraftin a descent configuration with flight characteristics for descent toconclude a flight (e.g. FIG. 17A). The method may also compriseconfiguring the aircraft in a third configuration for flight in modifiedoperating conditions (e.g. FIG. 17C); each flight configuration providesflight characteristics for flight in the expected/forecast operatingconditions. As indicated, the descent configuration is at leastsubstantially the same as the ascent configuration.

According to an exemplary embodiment shown representationally andschematically in FIGS. 22A-C, a method of operating a reconfigurablemulti-rotor unmanned aircraft for flight characteristics on a missionhaving multiple segments in operating conditions may comprise the stepsof configuring the aircraft in first configuration with flightcharacteristics for the first mission segment (e.g. FIG. 22A);configuring the aircraft in a second configuration with flightcharacteristics for the second mission segment (e.g. FIG. 22B);configuring the aircraft in a third configured with flightcharacteristics for the third mission segment (e.g. FIG. 22C). Eachflight configuration may comprise the use of a different number ofrotors of the rotor system and/or a different rotor positionconfiguration. According to an exemplary embodiment as shownrepresentationally and schematically in FIGS. 22A-C, the aircraft is ofa type having at least six rotors (e.g. an octa-copter with eight rotorsin total); the first configuration comprises use of more than six rotors(e.g. eight rotors for a relatively large payload delivery); the secondconfiguration comprises use of six rotors; and the third configurationcomprises use of fewer than four rotors.

As indicated according to the exemplary embodiments, availableconfigurations of the reconfigurable UAV/craft may be implemented forother purposes/segments of a mission; available configurations aredetermined in view of the design/construction and capacity of theUAV/craft (and operating conditions). Configurations of thereconfigurable UAV/craft for a mission may be determined according to amission plan (e.g. before the operation/flight of a mission) or asdetermined during flight/operation on a mission in response to operatingconditions.

According to an exemplary embodiment of a method of operation/managementof a reconfigurable UAV/craft, the reconfiguration of position of atleast one rotor of the rotor system can be performed during operation ofthe aircraft; for example, the reconfiguration of position of at leastone rotor may be performed during operation in response to changedperformance of a rotor such as a failing or failed rotor (e.g. tocompensate for loss of thrust of a rotor and/or to restore or to providestability for flight dynamics). The reconfiguration of position of atleast one rotor can be performed during operation of the reconfigurableUAV/craft in an effort to change flight characteristics (e.g. to modifyflight dynamics, modify drag, balance mass properties, reduce energyuse, improve energy efficiency, improve performance, increase maximumvelocity, counteract weather effects, etc.); the reconfiguration mayprovide for a balancing or rebalancing of the aircraft and payload (seeFIGS. 21A-D) (for example in response to mass property/inertia effectsof the payload on flight dynamics/characteristics such as due tomoving/swaying/lagging of payload suspended from the aircraft or ifthere is a mass change due to a leak or loss of payload) and/or during amission to rebalance mass properties after partial delivery of acomposite (multi-item) payload (see FIGS. 22A-C).

Operation/Management Method—Reconfiguration forMalfunctioning/Inoperable Rotor

According to an exemplary embodiment of a method of operation/managementof a reconfigurable UAV/craft, the determination to reconfigure therotor system may result from a malfunction of an aircraft system orsubsystem. For example, a malfunction may comprise of (a) the rotorunable to provide commanded rotation speed; (b) the rotor unable toprovide expected thrust; (c) the rotor unable to be given intendedpitch; (d) the rotor unable to be positioned to the intended rotorposition. A malfunctioning/inoperable rotor may be caused by a failingpower plant (e.g. motor or engine) or energy storage system (e.g. fuelor battery problem) or other causes such as impact with an object,improper maintenance/service, defective component, etc.

According to an exemplary embodiment of the method ofoperation/management of the reconfigurable UAV/craft the rotor that ismalfunctioning or becomes inoperable may be shut down (and repositionedrelative to the base and/or each other rotor) and at least oneoperational rotor may be repositioned to reestablish a balancedconfiguration for the UAV/craft; according to any preferred embodiment,after reconfiguration the UAV/craft is able to operate in thereconfigured position to compensate for the loss of function of thenon-operational/malfunctioning rotor. See FIGS. 30-34B.

According to an exemplary embodiment, the reconfigurable UAV/craftsystem will comprise a monitoring system to detect potential rotor/rotorsystem issues or other problems before (or immediately upon) a completemalfunction (e.g. so that a nearly immediate response may be initiated).See FIGS. 25 and 26. The monitoring system of the UAV/craft may evaluate(e.g. in real time from sensors/devices) data representative of suchparameters as (a) rotational speed of rotor; (b) force at rotorbearings; (c) force applied at rotor mount; (d) vibration at rotor; (e)temperature of rotor motor system. Other operational parameters may bemonitored to determine the status/condition and health of components ofthe UAV/craft system including the rotor system using any of a widevariety of sensors/detectors/devices (e.g. load cells, stress/strainsensors, accelerometers, vibration sensors, electronic detectors,video/visual monitoring, etc.) and methodologies presently in use,including with aircraft systems. See e.g. U.S. Pat. No. 8,775,013 titled“System and Method for Acoustic Signature Health Monitoring of UnmannedAutonomous Vehicles (UAVS)” (acoustic monitoring of UAV/aircraftsystems). The detector/sensor D of the monitoring system is shownrepresentationally and schematically according to an exemplaryembodiment in FIGS. 1 and 2 (e.g. at or adjacent to a rotor, boom,joint, etc.)

According to an exemplary embodiment of a method of operation/managementof a reconfigurable UAV/craft, if a malfunctioning rotor is detected bythe monitoring system in advance of the malfunction it may be possiblefor responsive corrective action to be determined/commanded and takenprior to a larger or more complete failure (e.g. prior to themalfunctioning rotor becoming totally inoperable) or in any event sothat the control system is better able to manage the situation andmaintain flight operation/stability of the reconfigurable UAV/craft.According to the method of operation/management as indicated, thereconfiguration of position of at least one operational rotor can beperformed in response to predicted or anticipated (futurepossible/probable) malfunction of a rotor (e.g. see FIG. 30); thereconfiguration of rotor position may be commanded or directed by thecontrol system at or in the early stages of a malfunction (e.g. if amalfunction is in process of occurring gradually the control system willhave time gradually to implement corrective action such as amodification of rotor/boom configuration as will permit more stablecontrol/maintenance of flight characteristics/stability in thesituation).

According to an exemplary embodiment a method of reconfiguringselectively reconfigurable aircraft with a rotor system with at leastone rotor that is at least partially malfunctioning may comprise thesteps of identifying the rotor that is malfunctioning; identifying arotor that is able to function (and is in an initial position);repositioning at least one functional rotor to a reconfigured position.According to the exemplary embodiment, the rotor system with at leastone functional rotor after reconfiguration (e.g. in the reconfiguredposition) is able to compensate for the loss of function of themalfunctioning rotor. According to a preferred embodiment, the aircraftis able to remain in flight/operation without thrust/lift otherwisecontributed/available to be provided by the malfunctioning/inoperablerotor; at least one functional rotor when repositioned to thereconfigured position is able to compensate for the loss of contributionof thrust/lift resulting from the malfunctioning/inoperable rotor.

According to an exemplary embodiment, during or in coordination withreconfiguration of the reconfigurable UAV/craft themalfunctioning/inoperable rotor of the rotor system may be retracted orstowed (see FIGS. 6B/C and 6D/E).

Materials of Construction

According to an exemplary embodiment, the base/structure, frame,arms/booms/members, mechanisms, rotor system, and other components ofthe UAV/craft will be made (e.g. formed, constructed, etc.) frommaterials that are suitable for use in aircraft applications (i.e.materials such as carbon fiber/composites, kevlar, engineered plastics,high-strength polymers/plastics, light-weight/density metal alloys,aluminum, titanium, steel, etc.) as known and used in the art (now andin the future).

Fleet Management System

Referring to FIG. 29, a system for management of a fleet of multiplereconfigurable UAV/craft is shown representationally and schematicallyaccording to an exemplary embodiment.

According to an exemplary embodiment, the fleet management system isimplemented by a computing system (see FIG. 24) over a network and touse data from UAV/craft systems (see FIGS. 25-28B). The fleet managementsystem is able to configure and deploy reconfigurable UAV/craft toperform missions; the fleet management system may also managemaintenance and repair of UAV/craft in the fleet as well as storage ofUAV/craft no longer in use. According to an exemplary embodiment, thefleet will comprise multiple units of the same/identical or similar typeUAV/craft that individually and/or collectively can be configured andreconfigured according to needs and objectives as part of the fleetmanagement function. For example, a fleet having three identical/similarUAV/craft and three different missions to perform may be managed so thateach individual UAV/craft is configured and programmed in a differentmanner to perform one of the different missions.

According to an exemplary embodiment where each UAV/craft is anocta-copter (see FIGS. 22A-C), one UAV/craft may operate on a missionsuch as carrying a substantial payload as an octa-copter (see FIG. 22A);one UAV/craft may operate as a hexa-copter on a mission with a lesserpayload and/or longer route (see FIG. 22B); one UAV/craft may operate asa quad-copter on a mission with a surveillance/monitoring function wherethe payload is a video monitoring system (see FIG. 22C). Each UAV/craftmay, for a subsequent mission, be reconfigured and reprogrammed in adifferent manner.

According to an exemplary embodiment (as indicated schematically in FIG.29), each UAV/craft in the fleet is able to be configured/programmed andreconfigured/reprogrammed to operate as a multi-function device toperform multiple types of missions (e.g. route/duty obligations) servingvarious needs/objectives while sharing data/analytics. According to anexemplary embodiment, the fleet management system is able to assignmissions (e.g. routes/duties) to individual UAV/craft in the fleet in anefficient manner in view of the configuration options for eachUAV/craft.

When not in use the reconfigurable UAV/craft in the fleet may be put ina storage configuration with all rotors retracted. See FIG. 6E.

Incorporation of Present Technology/Systems

The system and method according to exemplary and alternative embodimentsmay be configured to integrate or operate with present known (and/orfuture) systems and technology, for example, systems foroperating/monitoring and transforming UAV/craft (e.g. U.S. PatentApplication Publication No. 2014/0263823 titled “Transformable AerialVehicle”, U.S. Pat. No. 7,922,115 titled “Modular Unmanned Air-Vehicle”,U.S. Patent Application Publication No. 2014/0129059 titled “Method andApparatus for Extending the Operation of an Unmanned Aerial Vehicle”),systems for monitoring the state of operation/condition of an aircraft(e.g. U.S. Pat. No. 8,775,013 titled “System and Method for AcousticSignature Health Monitoring of Unmanned Autonomous Vehicles (UAVS)”),robotic arm systems/mechanisms (e.g. U.S. Pat. No. 8,758,232 titled“Robotic Arm”), systems for adjusting for rotating blades/vanes (e.g.U.S. Pat. No. 2,473,134 titled “Adjustable Rotor Blade”, U.S. Pat. No.2,844,207 titled “Adjustable Fan Blade Assembly”), and mechanisms formoving/manipulating mechanical elements and members/components (e.g.U.S. Pat. No. 8,534,147 titled “Electromotive Linear Drive”, U.S. Pat.No. 4,614,128 titled “Linear Drive Device with Two Motors”, U.S. Pat.No. 5,409,269 titled “Ball Joint Mechanism”, U.S. Pat. No. 6,101,889titled “Ball Screw and Nut Linear Actuator Assemblies and Methods ofConstructing and Operating Them”, U.S. Pat. No. 6,238,124 titled“Locking Joint Mechanism”, U.S. Pat. No. 4,890,713 titled “Pan and TiltMotor for Surveillance Camera”). Such systems/technology and patentdocuments are incorporated by reference in the present application asbackground for the present inventions.

Related Applications (Incorporation by Reference)

The following commonly-owned (at present) U.S. patent applications arelisted and incorporated by reference in the present application: (a)U.S. patent application Ser. No. 14/501,302, titled SYSTEM AND METHODFOR ADMINISTRATION AND MANAGEMENT OF AN AIRSPACE FOR UNMANNED AIRCRAFT,naming R. Hyde et al. as inventors, filed Sep. 30, 2014 is related toand incorporated by reference in the present application; (b) U.S.patent application Ser. No. 14/501,343, titled UNMANNED AIRCRAFTCONFIGURED FOR OPERATION IN A MANAGED AIRSPACE OF FLYWAY, naming R. Hydeet al. as inventors, filed Sep. 30, 2014 is related to and incorporatedby reference in the present application; (c) U.S. patent applicationSer. No. 14/501,365, titled SYSTEM AND METHOD FOR OPERATION OF UNMANNEDAIRCRAFT WITHIN A MANAGED AIRSPACE OR FLYWAY, naming R. Hyde et al. asinventors, filed Sep. 30, 2014 is related to and incorporated byreference in the present application; (d) U.S. patent application Ser.No. TBD, titled SYSTEM AND METHOD FOR OPERATION AND MANAGEMENT OFRECONFIGURABLE UNMANNED AIRCRAFT, naming R. Hyde et al. as inventors,filed Dec. 4, 2014 is related to and incorporated by reference in thepresent application.

It is important to note that the construction and arrangement of theelements of the inventions as described in system and method and asshown in the figures above is illustrative only. Although someembodiments of the present inventions have been described in detail inthis disclosure, those skilled in the art who review this disclosurewill readily appreciate that many modifications are possible withoutmaterially departing from the novel teachings and advantages of thesubject matter recited. Accordingly, all such modifications are intendedto be included within the scope of the present inventions. Othersubstitutions, modifications, changes and omissions may be made in thedesign, variations in the arrangement or sequence of process/methodsteps, operating conditions and arrangement of the preferred and otherexemplary embodiments without departing from the spirit of the presentinventions.

It is important to note that the system and method of the presentinventions can comprise conventional technology (e.g. aircraft design,construction, components, mechanisms, frames/systems, energy/powersystems, monitoring/sensors, materials, control systems, computingsystems, telecommunication systems, networking technology, data storage,data transmission, data/file structures/formats, systems/software,application programs, mobile device technology, etc.) or any otherapplicable technology (present or future) that has the capability toperform the functions and processes/operations indicated in the FIGURES.All such technology is considered to be within the scope of the presentinventions.

In the detailed description, reference is made to the accompanyingdrawings, which form a part hereof. In the drawings, similar symbolstypically identify similar components, unless context dictatesotherwise. The illustrative embodiments described in the detaileddescription, drawings, and claims are not meant to be limiting. Otherembodiments may be utilized, and other changes may be made, withoutdeparting from the spirit or scope of the subject matter presented here.

While various aspects and embodiments have been disclosed herein, otheraspects and embodiments will be apparent to those skilled in the art.The various aspects and embodiments disclosed herein are for purposes ofillustration and are not intended to be limiting, with the true scopeand spirit being indicated by the following claims.

The invention claimed is:
 1. A method of reconfiguring selectivelyreconfigurable aircraft for unmanned flight comprising the steps of: (a)positioning a first rotor on a first boom coupled to a base; (b)positioning a second rotor on a second boom coupled to the base; (c)modifying the position of at least one rotor relative to the base;wherein position of the rotor relative to the base is modifiable by (1)translation of the rotor relative to the boom; so that flightcharacteristics are modifiable by reconfiguration of the position of atleast one rotor relative to the base.
 2. The method of claim 1 whereinposition of the rotor on a boom is modifiable by at least one of: (2)translation of the boom relative to the base; (3) pivoting of the boomrelative to the base; (4) retraction of the boom relative to the base;(5) pivoting of the rotor relative to the boom; (6) raising the heightof the boom relative to the base; (7) lowering the height of the boomrelative to the base; (8) rotating the rotor relative to boom; and (9)rotating the boom relative to the base.
 3. The method of claim 1 furthercomprising at least one of: positioning a third rotor on a third boomcoupled to the base; positioning a fourth rotor on a fourth boom coupledto the base; positioning a fifth rotor on a fifth boom coupled to thebase; positioning a sixth rotor on a sixth boom coupled to the base;positioning a seventh rotor on a seventh boom coupled to the base; andpositioning an eighth rotor on an eighth boom coupled to the base. 4.The method of claim 1 wherein flight characteristics are modifiable byat least one of: (a) changing rotation speed of at least one rotor; (b)changing pitch of vanes of at least one rotor; (c) changing position ofthe rotor relative at least one other rotor; (d) modifying thepositioning of one boom relative to another boom; and (e) modifying thepositioning of one rotor relative to the base.
 5. The method of claim 1wherein flight characteristics comprise at least one of aerodynamicprofile, maneuverability, available thrust, available lift, energyconsumption, energy efficiency, mass, mass properties, center of mass,center of gravity, balance point, stability, controllability, controlaxes, maximum relative ground velocity, maximum relative air speed,ascent rate, descent rate, sink rate, flight altitude, aerodynamic drag,number of operational rotors, control system type, equipment status. 6.The method of claim 1 wherein each rotor comprises a set of bladesrotating on an axis, the method further comprising adjusting pitch ofblades of the rotor.
 7. The method of claim 1 further comprisinganticipating rotor malfunction so that reconfiguration of the rotoroccurs before malfunction.
 8. The method of claim 1 wherein flightcharacteristics are modifiable in response to operating conditions for amission.
 9. The method of claim 8 wherein operating conditions for amission comprise at least one of operability of each rotor, energystorage capacity, remaining energy storage, payload profile, payloadmass, payload type, payload shape, payload size, payload changes, route,altitude, traffic, weather conditions, weather effects, wind velocity,wind direction, distance of mission, remaining distance of mission, timefor mission, remaining time for mission, fuel storage capacity,remaining fuel, energy storage capacity, remaining stored energy. 10.The method of claim 8 further comprising the step of responding to achange in operating conditions.
 11. The method of claim 10 whereinresponding comprises the step of changing rotor speed.
 12. The method ofclaim 11 wherein if change in rotor speed is beyond a limit ofoff-design-point rotor speed then responding further comprises changingrotor position.
 13. A method of reconfiguring selectively reconfigurableaircraft for unmanned flight having a set of rotors configured toprovide lift for propulsion with at least one rotor that is at leastpartially malfunctioning comprising the steps of: (a) anticipating rotormalfunction; (b) identifying the rotor that is malfunctioning; (c)identifying at least one functioning rotor that is in an initialposition; and (d) repositioning the at least one functioning rotor fromthe initial position to a reconfigured position so that reconfigurationof the at least one functioning rotor occurs before malfunction; so thatbefore malfunction the at least one functional rotor when afterreconfiguration in the reconfigured position compensates for the loss offunction of the malfunctioning rotor.
 14. The method of claim 13 whereinthe aircraft comprises a base and wherein repositioning of the at leastone functioning rotor comprises positioning the at least one functioningrotor relative to the base.
 15. The method of claim 13 whereinmalfunctioning comprises at least one of the rotor that ismalfunctioning being (a) unable to provide commanded rotation speed; (b)unable to provide expected thrust; (c) unable to be given intended bladepitch; and (d) unable to be positioned to the intended rotor position.16. The method of claim 13 further comprising monitoring at least one of(a) rotational speed of the rotor, (b) force at rotor bearings, (c)force applied at rotor mount, (d) vibration at the rotor, (e)temperature at the rotor; (f) performance of motor for the rotor. 17.The method of claim 13 wherein identifying comprises monitoring thatincludes at least one of acoustic monitoring, visual monitoring,vibration monitoring, stress/strain monitoring, and data monitoring. 18.The method of claim 13 further comprising the step of retracting themalfunctioning rotor by at least one of a translating movement and apivoting movement.
 19. The method of claim 13 wherein repositioning theat least one functioning rotor comprises at least one of (1) extendingthe boom; (2) retracting the boom; (3) elevating the boom relative tothe base; (4) lowering the boom relative to the base; (5) rotating theboom in a plane relative to the base; (6) translating the rotor alongthe boom; (7) tilting the rotor relative to the base; (8) rotating therotor relative to boom; (9) rotating the boom relative to the base. 20.The method of claim 13 further comprising the step of hovering theaircraft during the step of repositioning at least one rotor.
 21. Themethod of claim 13 further comprising at least one of repositioningpitch of blades of the functional rotor; repositioning pitch of vanes ofthe functional rotor; regulating rotational speed of the functionalrotor; and restricting thrust produced by the functional rotor.
 22. Themethod of claim 13 wherein flight characteristics are modifiable by atleast one of (1) translation of the rotor relative to the boom; (2)pivoting of the boom relative to the base; (3) translation of the boomrelative to the base; (4) retraction of the boom relative to the base;(5) pivoting of the rotor relative to the boom; (6) raising the heightof the boom relative to the base; (7) lowering the height of the boomrelative to the base; (8) rotation of the rotor relative to the base;(9) rotational twist of the boom relative to the base; (10) changingspacing of the rotor relative to another rotor; (11) changing incline ofthe rotor; (12) changing horizontal position of the rotor relative tothe base; (13) changing vertical position of the rotor relative to thebase; (14) moving the rotor inward relative to the base; (15) moving therotor outward relative to the base; (16) tilting the rotor; (17)changing rotor thrust; (18) disabling the rotor; (19) changing pitch ofvanes of at least one of the rotors; (20) changing rotation speed of atleast one of the rotors; and (21) changing position of the rotorrelative at least one other rotor.
 23. The method of claim 13 whereinflight characteristics comprise at least one of aerodynamic profile,maneuverability, available thrust, available lift, energy consumption,energy efficiency, mass, mass properties, center of mass, center ofgravity, balance point, stability, controllability, control axes,maximum relative ground velocity, maximum relative air speed, ascentrate, descent rate, sink rate, flight altitude, aerodynamic drag, numberof operational rotors, control system type, equipment status.
 24. Themethod of claim 13 wherein flight characteristics are modifiable inresponse to operating conditions for a mission.
 25. The method of claim24 wherein operating conditions for a mission comprise at least one ofoperability of each rotor, energy storage capacity, remaining energystorage, payload profile, payload mass, payload type, payload shape,payload size, payload changes, route, altitude, traffic, weatherconditions, weather effects, wind velocity, wind direction, distance ofmission, remaining distance of mission, time for mission, remaining timefor mission, fuel storage capacity, remaining fuel, energy storagecapacity, remaining stored energy.
 26. A method of operating areconfigurable multi-rotor unmanned aircraft with each rotor in a rotorposition on a movable boom relative to a base of the aircraft for flighton a mission to provide intended flight characteristics in operatingconditions comprising the steps of: (a) configuring the aircraft in afirst configuration with intended flight characteristics for ascent tostart a flight; (b) configuring the aircraft in a second configurationwith intended flight characteristics for flight in operating conditions;wherein the first configuration comprises a first rotor position for atleast one rotor; wherein the second configuration comprises a secondrotor position for the at least one rotor; wherein position of the atleast one rotor relative to the base is modifiable by (1) translation ofthe rotor relative to the boom.
 27. The method of claim 26 furthercomprising at least one of configuring the aircraft in a thirdconfiguration with intended flight characteristics for descent toconclude a flight; and configuring the aircraft in a fourthconfiguration with flight characteristics for flight in operatingconditions.
 28. The method of claim 26 wherein flight characteristicscomprise at least one of aerodynamic profile, maneuverability, availablethrust, available lift, energy consumption, energy efficiency, mass,mass properties, center of mass, center of gravity, balance point,stability, controllability, control axes, maximum relative groundvelocity, maximum relative air speed, ascent rate, descent rate, sinkrate, flight altitude, aerodynamic drag, number of operational rotors,control system type, equipment status.
 29. The method of claim 26wherein flight characteristics are modifiable by at least one of (1)pivoting of the boom relative to the base; (2) retraction of the boomrelative to the base; (3) pivoting of the rotor relative to the boom;(4) raising the height of the boom relative to the base; (5) loweringthe height of the boom relative to the base; (6) rotation of the rotorrelative to the base; (7) rotational twist of the boom relative to thebase; (8) changing spacing of the rotor relative to another rotor; (9)changing incline of the rotor; (10) changing horizontal position of therotor relative to the base; (11) changing vertical position of the rotorrelative to the base; (12) moving the rotor inward relative to the base;(13) moving the rotor outward relative to the base; (14) tilting therotor; (15) changing rotor thrust; (16) disabling the rotor; (17)changing pitch of vanes of at least one of the rotors; (18) changingrotation speed of at least one of the rotors; (19) changing position ofthe rotor relative at least one other rotor; and (20) translation of theboom relative to the base.
 30. The method of claim 26 furthercomprising: carrying a payload having a mass; and modifying the positionof at least one rotor to compensate for at least one of the mass of thepayload and position of the mass of the payload.
 31. The method of claim26 wherein reconfiguration of rotor position is performed during amission to rebalance mass properties after partial delivery of apayload.
 32. The method of claim 26 wherein flight characteristics aremodifiable in response to operating conditions for a mission.
 33. Themethod of claim 32 wherein operating conditions for a mission compriseat least one of operability of each rotor, energy storage capacity,remaining energy storage, payload profile, payload mass, payload type,payload shape, payload size, payload changes, route, altitude, traffic,weather conditions, weather effects, wind velocity, wind direction,distance of mission, remaining distance of mission, time for mission,remaining time for mission, fuel storage capacity, remaining fuel,energy storage capacity, remaining stored energy.